JPRS ID: 8666 TRANSLATION WORLD SPACE RESEARCH VOL.1, 1970-1973

• Document Type: CREST
• Collection: JPRS
• Document Number (FOIA) /ESDN (CREST): CIA-RDP82-00850R000100090025-4
• Release Decision: RIF
• Original Classification: U
• Document Page Count: 215
• Document Creation Date: November 1, 2016
• Sequence Number: 25
• Content Type: REPORTS

APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4
19 SFPTF"RFR t979
i I I
YOI. i, 1971-073

~ nir ot
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
= JPRS L/8666
- 18 September 1979
J
Translation
WORLD SPACE RESEARCH
Vol. 1, 1970-1973
itz
~
\

~..y~ � /
I 0
FBI$ FOREIGN BROADCAST lNFORMATION SERVICt
FOR OFFICIAL USE ONLY
V
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
NOTE
JPRS publications contain information primarily from foreign
: newspapers, periodicals and books, but also from news agency
transmissions and broadcasts. Materials from foreign-language
= sources are translated; those from English-language sources
- are transcribed or reprinted, with the original phrasing and
= other characteristics retained.
Headlines, editorial reports, and material enclosed in brackets
' are supplied by JPRS. Processing indicators such as [Text]
or [Excerpt] in the first line of each item, or following the
. last line of a brief, indicate how the original information was
- processed. Where no processing indicator is given, the infor-
= mation was summarized or extracted.
_ Unfamiliar names rendered phonetically or transliterated are
~ enclosed in parentheses. Words or names preceded by a ques-
tion mark and enclosed in parentheses were not clear in the
J original but have been supplied as appropriate in context.
_ Other unattributed parerichetical notes wittiirL the body of an
= item originate with the source. Times withir, i.tems are as
= given by source.
_ The contents of this publication in no way represent the poli-
cies, views or attitudes of the U.S. Government.
For fsrther information on report content
call (703) 351�-2938 (economic); 3468
(political, sociological, military); 2726
(life sciences); 2725 (physical sciences).
COPYRIGHT LAWS AND REGULATIONS GOVERNING OWNERSHIP OF
MATERIALS REPRODUCED HEREIN REQUIRE THAT DISSEMINATION
- OF THIS PUBLICATION BE RESTRICTED FOR OFFICIAL USE ONZY.
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
~ JPRS L/8666
~ 18 September 1979
= WORLD SPACE RESEARCH _
= VoL, 1, 1970-1973 _
~
This special report contains translations of ar:._;les extracted from the -
= YEZHEGODNIKI BOL'SHOY SOVETSKOY ENTSIKL~OPEDII [Great Soviet Encyclopedia "
r-
- Yearbooks] since 1971 that deal with the space exploration programs of -
selected nations throughout the world. Entries for each year are divided -
into sections for both "Soviet" and "Non-Soviet" space research. _
~
- Volume I covers developments for the period 1970-1973; Volume II will cover
- 1974-1978. Supplements will be published annuaily as the yearbooks become ,
~ available for translation. -
CONTENTS PAGE -
_ Soviet Space Research in 1970
(L. Lebedev) 1
= Non-Soviet Space Research in 1970
- (V. Shitov) 29 -
~ Soviet Space Research in 1971 -
(L. Lebedev) 49 -
Non-Soviet Space Research in 1971 _
(D. Gol'dovskiy) 78
Soviet Space Research in 1972 -
- (L. Lebedev) 106 _
Non-Soviet Space Research in 1972 -
_ (D. Gol'dovskiy) 126
Soviet Space Research in 1973 f-
(L. Lebedev) 156 -
- Non-Soviet Space Research in 1973
(D. Gol'dovskiy) 178
- - a - [I - USSR - A FOUO] =
[III - US5R - 21J S&T FOUO] :
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FUR QFrTCIAL USE ONLY ~
SOVIET SPACE RESEARCH IN 1970
I Moscow YEZHEGODNIK BOL'SHOY SOVETSKOY ENTSIKLOPEDII in Russian No 15, 1971 ~
~ pp 492- 503
I
-i [Article by L. Lebedev]
-'I
[Text] in 1970 the "Soyuz-9" manned transport ship and automatic stations
to study the moon, Venus and near-earth and interplanetary space were launched. `
- Launchings of artificial earth satellites for purely scientific and applied =
purposes continued.
_ The flight of "Soyuz-9" took place 1-19 June. In the 18-day scientific ex-
: periment the scientists set the goal of studying the effect of the prolonged
- exposure of a set of surrounding factors on the human organism, and primarily
- of verif.ying man's ability to actively work under conditions of weightless-
- ness for a long time. It was important to also investigate the process of
- man's transition to the conditions of earth's gravity.
The flight program of "Soyuz-9" included a vast complex of scientific and -
' technical, medical and biological studies, and experiments that were begun - in the previous space flights. -
The "Soyuz-9" spacecraft was launched at the Baykonur Cosmodrome on 1 June ~
- at 2200 hours.* The craft was piloted by the commander A. G. Nikolayev and -
the flight engineer, Candidate of Technical Sciences V. I. Sevast'yanov.
During the flight of "Soyuz-9" a large number of dynamic operations were
performed which were associated with its orientation. As a rule, they were
performed using manual control. The cosmonauts conducted tests of the star
sensor and the opticoelectronic instrument created for purposes of orienting
~ the craft to earth during its flight over the earth's shaded side. In going -
through the methods and means of autonomous navigation Nikolayev and Sevas- -
t'yanov made various measurements, determined tne orbital parameters and cal-
_ culated the necessary trajectory corrictions. On-board computer resources -
were used for a rapid solution to the navigational tasks. _
_ * Here and further--Moscow Time.
1
FOR OFFICIr,L L'SE UvLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FUK UFFICiAL IJSE ODiLY -
\
A number of experiments were associated with an investigation of the design
characteristics of the craft. The cosmonauts measured the design deforma- ~
tions produced by the conditions of vacuum and solar heating, studied the =
= work of the precision mechanisms and optic assemblies, tested the high-pre-
. cision illuminators that guarantee the reliable operation of the optic in-
, struments, and evaluated the effect of aerodynamic and gravity disturbances
on the dynamic characteristics and controllability of the craft; they also
~ tested different systems of long-term life-support. -
To study the potentialities for man's living and working normally under con-
ditions af a prolonged space flight the cosmonauts performed experiments to
= study the functions of the vestibular apparatus, the dynamics of arterial -
pressure, external respiration, the nature of pain sensitivity of the skin,
the contrast sensitivity of the eyes, and the preservation of the charac- _
teristics of the visual apparatus. Studies were also made on the muscular
' strength of the arms and musculo-articular sensitivity. With the help of
a special cybernetic device a study was made of the dynamic fi.inctions of man
as an element in the control system. In order to construct the optimal life-
- support systems and develop scientifically substantiated rations for food -
and water consumption the energy expenditures of the cosmonauts during the -
_ flight were calculated.
Experiments of national economic importance occupied a large place. On the =
. 188th orbit, when "Soyuz-9" was over the Indian Ocean, a complex equipment
- was conducted in which, besides the crew of "Soyuz-9," the "Meteor" satel-
lite and the scientific research ship "Akademik Shirshov" participated. -
Radiosondes were launched from the ship to measure the temperature and wind _
; velocity in different layers of the atmosphere. The "Meteor" AES [artificial _
earth satellite], having flown at the same time over this territory, trans- _
_ mitted a series of television photograplis from an altitude about 630 lan, -
- while the cosmonauts observed this region from a lower orbit. (A similar _
experiment was conducted by the crew of "Soyuz-7" in October 1969). ~
- F
Joint photography of the earth from meteorological satellites was also con-
` ducted over Africa, the Atlantic Ocean, and over the southern part of the
Indian Ocean. During the flight the cosmonauts observed cyclones, recorded
- dust storms, and reported to earth observations on the state of the weather ~
in individual regions of the globe. They photographed geographical and geo- _
_ logical objects of the earth's surface. In the comprehensive experiment,
photographs of regions of the North Caucasus, the Caspian and Aral seas, -
Kazakhstan and West Siberia were taken simultaneously from on board Soyuz-9
- and from airplanes. Scientific experim.ents to study near-earth space included -
- photographing of the earth's horizon, as well as the moon on the background
- of the earth's horizon. During the flight studies were made of the bright-
- ness of different objects in the visual region of the spectrum. The given
- experiment was set up in order to investigate the possibility of creating -
_ new systems of astronavigation. It is also needed by meteorologists to -
_ determine the upper border of clouds in order to develop a technique fo:
_ automatically processing the information received from meteorological sacel- =
_ lites. A total of over 50 different experiments were made during the flight, -
, tahereby each was performed several times. -
2
FOR OFFICIAL U5E ONL!'
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FUK OFF7:C1AL USI? UN1,Y
,
. "Soyuz-9" landed on 19 June at 14.59 75 km to the west of Karaganda. As _
the scientists eYpected, after a prolonged stay in a state of zero gravity -
= speciFic difficu].ties developed in the cosmonauts that were associated with _
% the adaptation of the organism to life on earth. In the first 2-3 days -
= Nikolayev and Sevast'yanov noted that their sensations were analogous to -
- the sensations of a man who had been on a centrifuge under the influence -
of a G-force of 2-2.5 units. The condition of the organism had practically =
- been normalized by the lOth day after their return to earth. -
f The flight of the (AS) "Luna-16" automatic station in an earth-moon-earth -
= orbit took place 12-24 September (it was launched 12 September at "1626
hours). The flight made it possible to solve the most complicated scien- -
tific and technical problem of astronautics--intake of samples of lunar
- rock by automatic means, and delivery of these samples to earth. The Luna- "
16 AS was designed as a landing stage (LS) with a soil intake device (SID) =
= on which a"Luna-Zemlya" rocket with a recoverable apparatus (RA) was mounted.
= The station when it lands on the moon weights 1880 kg. This LS is a unified ~
aggrega.te capable of transporting to the moon automatic systems with scien- ~
tific apparatus of various designatiens. It is a multipurpose rocket block _
- that has a liquid-propellant rocket engine, a system of tanks with propel- -
- lant components, instrument compattments, and cushioning supports for land- _
- ing on the moon. The propulsion system of the LS consists of the main en- - gine of multiple engagement with controllable chrust for deceleration, and
two low-thrust engines that operate in the final stage of the landing. In =
~ the instrument compartments of the LS there are computing and gyroscopic =
instruments of the control and stabilization systems, electronic instruments _
- of the orientation system, radio transmitters and receivers of the on-board ~
~ radio measuring complex that operate in several wavelength ranges, a program-
time device to control the operation of all systems and aggregates, chemi- -
= cal sources of electricity and current transduvers, components of the thermo-
- regulation system, autonomous radio facilities to measure altitude, and the
= horizontal and vertical velocity components during the landing on the lunar =
_ surface, as well as scientific apparatus to make temperature and radiation -
. measurement both on the segment of ttie flight to the moon, and on its sur- -
- face. On the outer LS surface there are antennas of the on-board radio com-
= p1Ex, jet-propelled micro-engines of the orientation and stabilization sys- .
tems, tanks with a supply of working fluid for the microengines, and optic
- gauges of the orientation system. In the take-off of the rocket "Luna- -
- Zemlya" from the lunar surface the LS serves as a starting device.
The "Luna-Zemlya" rocket is a rocket block with liquid-propellant rocket
= engine (LPRE), and a system of spherical tanks with propellant components.
~ On the central tank is fastened a cylindrical instrument compartment, in
- which there are the electronic computing and gyroscope instruments of the
rocket's control system, the t�ansmitting, receiving, decoding, and program-
time instruments of the on-boa d raciio complex of the rocket, storage bat-
teries and current transducers, and instruments of the on-board automatics.
On the outer surface of the IC of the rocket four collapsible-whip receiv-
- ing-transmitting antennas are installed. The spherical recoverable apparatus
_ (RA), which is separated from the rockets by radio command during its flight
- back to earth, is attached by metal tension bands to the upper part af the
IC. 3
FOR OEFIC IAL U5E C)vLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FUR OFrICIAL US1: ONLY
The RA (Figure 2) is a metal ball on whose outer surface a heat-protective
, coating has been applied to protect the apparatus with the equipment installed
inside it from the effect of high temperatures during entry into the earth's
+ atmosphere. Inside the RA is divided into three insulated compartments.
In the largest volume compartment the%re are: radio direction finding trans-
= mitters that make it possible to find the RA during parachute re-entry and
= aFter landing on the earth, storage batteries, components of automatics, and
= an on-board programmer that controls putting the parachute system into opera-
_ tion. In the second compartment are located the folded parachute, four flex-
ible antennas of the direction finding transmitters, two elastic tanks
filled with gas that guarantee the necessary position of the RA on the earth's
surface after landing. The third compartment is a cylindrical container for
- lunar soil taken from the lunar surface. The container has a reception open-
_ ing, hermetically sealed by a special cover after the lunar rocks are placed
_ in it.
~ The SID (Figure 3) is installed on the landinb stage, and consists of three
main parts: a drill with a system of electrical drives and drill apparatus;
~ a probe on which the drill is attached; and drives moving the probe in ver-
= tical and horizontal planes. In the development of the SID special attention
- was focused on solving the task of creating a drill capable of drilling and
collecting samples of lunar soil of varying density--from loose (dust-like)
to hard, like the earth's basalt and hranites.
- A marker was installed on the LS of "Luna-16," and on the RA--a state sign
(Figure 8).
- The "Luna-16" AS was put into orbit as an artificial earth satellite by a
- more powerful satellite-launcher as compared to the satellite-launcher of
= the "Luna-9" AS and "Luna-13" AS (for a scheme of the flight of the "Luna-
; 16"AS see Figure 4). The apogee of the intermediate earth orbit was 212.2
_ km; the orbital inclination was 51�36'. The trajectory correction made on
12 September guaranteed the insertion of the "Luna-16" station at the cal-
_ culated point in circumlunar space, from which, due to the applied decelera-
- tion impulse it transferred to a circular selenocentric orbit with altitude
110 km, inclination relative to the plane of the lunar equation-70�, and
, orbital period--1 h 59 min.
_ On 18 and 19 September a manauver in circumlunar space was executed, as a -
= result of which the station switched to 2n elliptical orbit with parameters; -
= aposelene--106 km, periselena--15 km, inclination--71�, and orbital period--
- 1 h 54 min. After making trajectory measurements and the necessary orien-
" tation of the station at the calculated point in the orbit, the propulsion .
_ system was engaged, and "Luna-16," descending from orbit, began a- 250-
_ kilometer path above the lunar surface to the point of landing. Then the -
' engine was disengaged--vertical descent began (Figure 5). At altitude 600 m _
from the surface the main engine of the station again began to operate. The _
- thrust pattern here was altered according to the selected control progr.m -
- and the incoming information from the Doppler velocity gauge and radio ai-
- timeter. At altitude 20 m the velocity of the station was reduced roughly
to 2 m/s. Here the main LPRE was disengaged, and further deceleration oc-
- curred with the help of low-thrust engines. At altitude - 2 m they were _
4
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
roi. orrIcMt, ust: ovi.Y
s
Figure l. "Luna-16" Automatic Station Figure 2. Layout of Recoverable
Apparatus of "Luna-16" Station
Key:
1. Recoverable apparatus
2. Instrument compartment of
rocket
3. Propellant tanks of rocket
4. Controlling jets
5. Instrument compartment of
landing stage
6. Engine of "Luna-Zemlya" rocket
7. Engine of landing stage
8. Propellant tank
9. Telephotometer
10. Probe of drilling mechanism
11. Drilling mechanism
12. "Luna-Zemlya" rocket
13. Landing stage
14. Antenna
Key:
1. Housing of recoverable apparatus
2. Heat protection
3. Cover of parachute compartment
4. Parachute compartment
5. Container for lunar soil
6. Cover of container
7. Storage battery
8. Transmitters
9. Antenna switch
10. Antenna
disengaged by command from the gamma altimeter, and on 20 September at 0818
hours the "Luna-16" AS completed a soft landing on the surface of the moon
in the region of the Sea of Fei-ility. The selenographic coordinates of the
moon landing site: lat 0�41'S and long 56�18'E. The deviation from the
calculated landing point was 1.5 km.
S
FOR Ol FICI;,L U5E ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4
CJ � . 8 7

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FUR OFrICIAL USE ONLY
13
11
10 '
Figure 3. Scheme of Soil-Intake
Device of "Luna-16" AS
Key:
1. Recoverable apparatus
2. Starting position of probe and
drill
3. Ampule
4. Soil
5. Cover lock
6. Hsrmetir_ cover to ampule
7. Ampule positioning spring
8. Probe buffer
9. Operating position of drill
and probe
10. Drilling charge
11. Rotor
12. Screw feed
13. Drill casing
7
1:
1
~
Figure 4. "Luna-16" AS Flight Pattern
Key:
1. Acceleration
2. Earth-to-moon trajectory
3. Correction
4. Deceleration and transfer to
artificial lunar satellite orbit
5. Moon's orbit
6. Maneuvering in a circumlunar orbit
7. Deceleration and soft landing
8. Takeoff from moon`s surface
9. Moon-to-earth trajectory
10. Insertion into artificial earth
satellite orbit
11. Separation of recoverable apparatus
from rocket
12. Flight in artificial earth satel-
lite orbit
After the station had landed on the moon, a set of operations was implemented
_ that included measurement of the station orientation in relation to the local
vertical, and verfication of the functioning of different aggregates and on-
- board systems. Further, at the command from earth the SID by complex mani-
pulations provided contact of the electrical probe with the surface layer,
drilling of the soil to a depth of 35 cm, intake of the soil, and its d~-
livery to the container of the recoverable apparatus.
6
FOR OFFICIi,;. USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4
O 9

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FUR OF'FICIAL IISE ODILY
1 ~

~
/
I
I
I
1
1
1
~
A-2
~
~
s
0
e
t
~
~
3 4$ q
~
Key:
1.
2.
3.
4.
5.
6.
7.
Propulsion system turned off
Rotation of station ceases
Radioaltimeter and velocity
gauge turned on
Controlled descent phase
Main engines turned on
Low-velocity descent phase
Main engines turned off, low-
thrust engines turned on
Low-thrust engines turned off
Figure 5. "Luna-16" AS Lunar Landing Pattern
Figure 6. Overall View of Lunar Soil Transported by the "Luna-16" Station
On 21 September at 1043 hours the "Luna-Zemlya" rocket was launched auto-
- matically from the moon, and switched to a trajectory for the flight to
- earth. On 24 September, having separated from the space rocket, the RA en-
tered the dense atmospheric layers at 0810 hours. After aerodynamic decel-
" eration in the ballistic trajek:ory at altitude 14.5 lan the parachute system
was put into operation, and at 0826 hours the RA of the "Luna-16" station
- made a soft landing in the calculated region, 80 lan southeast of Dzhezkazgan.
. 7
FUR OFFICII,L USE UNLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR O.EFICIAL IISE ONLY
_ The lunar soil was transfezred to the Special Reception Laboratory of the
~ USSR Academy of Sciencesy where it was studied. The total weight of the
_ column of soil supplied by "Luna-16" was 101 g.
- Ttie drill was filled witn loose lunar soil (Figure 6)--regolith, which is
a dark gray (blackish) powder with varying grain size which is easily formed
= and sticks together in. individual loose clumps. This feature significantly
distinguishes the soil (regolith) from the earth's structureless dust; in
- this property it is similar to wet sand or the lumpy structure of the earth's
- soils. The graininess ot the regolith is increased with depth; grains with
an average size of about 0.1 mm predominate.
= A small part of the soil at the bottom of the borehold, at depth 35 cm, con-
sisted of large-grain material--the drill had touched solid rock or a separ-
ate large fragment of rock. The thickness of the regolith in the Sea of
Fertility, at the point of sampling of the lunar soil was not greater than
N 35 cm, and possibly reaches 0.5-1 m, or somewhat more than a meter. The
= specific weight of the regolith in the natural bed was defined as,- 1.17
- (1.20) g/cm3. By mechanical concentration its density can be brought to
~ 2.3 g/cm3. The specific heat capacity of regolith equals 0.177 cal/g�deg,
_ while the coefficient of heat conductivity in a vacuum equals 4.8�10'6
_ cal/s�cm�deg (with density p= 2.25 g/cm3 and t= 20-40�C).
The optic properties of the regolith were also investigated. The normal
albedo is altered from 0.86 in the ultraviolet region of the spectrum to
; 0.126 in the near infrared region, and for the visible light equals 0.107.
Such a value corresponds to soil somewhat lighter than is typical for lunar
_ seas on the average, but close to the ground determinations of albedo of
the Sea of Fertility in the region of the landing: for the Sea of Fertility
on the average the albedo equals 0.69, while in the region nearest to the
landing site of "Luna-16"--0.105.
Microscopic study af the lunar substance made it possible to separate two
= main sets of particles (Figure 7): particles of primary magmatic surface
rocks of *_he type basalts, and particles subject to noticeable transforma-
tions on the lunar surface. The first are characterized by a fresh habit
- observed on earth only on newly crushed samples of permanent rocks. They
do not carry traces of toughness, and have angular shapes. The second
= carry clear traces of fusion--sizter of complex shape, vitrified from the
surface, a noticeable number of spherical fused formations--solidified
_ drops of glass and metal habit.
In chemical composition the substance of the lunar soil is crushed rock of
- the basalt type. Comparative datl on the composition of the regolith and
crystalline rocks from the three lunar seas are given in Table l.
It is apparent from the da*_a of Table 1 that the sharpest difference in the
composition of rocks brought by "Luna-16" consists of the low Ti content.
It is practically the same with rocks of the Ocean of Storms, and almost
reduced by half as compared to the Sea of Tranquility.
8
T'OR 0'r'F7CIi,L liSE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FUR OFrICIAL USE ONLY
a
r-1
~
~
E-i
M
rn
-zr
ao
rn
1:1-
o
r-4
co
r-4
i
�rl r-{
1,
m
M
1.0
1~
-t
m
rl
N
N
O
I
44 rl 1
.
.
.
.
.
.
.
.
.
.
.
O�rl cd
r-I
v'1
Cy1
~O
CO
N
O
O
O
O
O
!-i C
d'
r-I
r-i
r-I
Ct N :J
a) a) a
cn w=
x

-
�rl
N
O
w I
00
Lr)
r-I
rn
N
O ^ O
rl
~t
r-1
N
d'
O
O
0)
p~

~ O
M
O
O
O
O
O
O
O
~
~
~
~
~
r-i
N O
U LJ
O Cn -
1
G '
N -I
~4 ~
~
-It
N
M
I~
u'1
C N
Na) 44 ~ aJ 41 O W W L4
v) cn O v] rn z U_ _
� oN lHa q I
N m -IT Ln .o r, oo rn or~
M M M c'f1 CY1 M cYl c*1 d' -T
46
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FGR OFFICIAL USE ONLY
CM splashed down in ttie Pacific Ocean at a point with coordinates lat.
= 21�39' S and long. 165�23' W 700 m from the calculated point. The flight
had lasted 142 h 54 min. The compartment splashed down normally, divers
_ were dispatched to it, and the astronauts were lifted on board a helicopter
_ which transported them to the aircraft carrier "Iwo Jima." A medical ex-
; amination showed that Lovell and Swigert were in good health, but in Haise
a certain health disorder was observed. All the astronauts were very fa-
=j tigued and had lost weight (2.3-4.5 kg). Due to the safe return President
i Nixon gave to the astronauts and to the ground crew in Houston that saved
i the flight, the "Medal of Freedom"--the highest civil award in the United
j States (this medal was also awarded to the crews of "Apollo 11" and "Apollo
12").
A special commission investigated the causes of the accident and wrote a
-j report with appropriate recommendations. In summarizing, it was noted that
this was the first flight with a malfunction in the manned transport ships
of the "Apollo" program; none of the tasks of the flight, with the exception
of the lunar landing of the final stage of the rocket, had been fulfilled.
The flight revealed the need for modifying the crafts in order to prevent
i fir.es in the oxygen medium, a certain moficiation in the second stage of
the rocket launcher (to prevent longitudinal oscillations in the liquid
oxygen lines), for a re-examination of the regulations governing the life-
style of the astronauts in the last weeks before the flight (in order, as
far as possible, to protect them from infection), and to make up the crews
from experienced test pilots (until crafts are made that are sufficiently
large to hold passengers). The safe return of the astronauts after such a
_ serious accident was valued by the United States specialists as a demonstra-
tion of the extensive technical capabilities of the "Apollo" ships, the ef-
ficiency of the ground crew in an emergency situation, and the courage and
high skill of the astronauts.
FOOTNOTES
- 1. Scanning Radiometer.
2. Flat Plate Radiameter.
- 3. Solar Proton Monitor.
4. Quarter-Orbit Magnetic Attitude Control System.
5. Magnetic Bias Control System
6. Of the four pre-vious launchings one was unsuccessful (18 May 1968)
_ 7. For an expansion of the des gnations of this as well as the instruments
listed below see YEZHEGODNIK BSE 1970, p 501.
_ 8. Frog Otolith Experiment Package.
47
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
are a result of the engagement of the engines of the last stage of the
rocket launcher which had to transport the satellite to the prescribed
synchronous orbit with inclination 9.9�.
_ 23. From materials of the report of President Nixon. In other sources
' this satellite is not mentioned.
24. It was noted in the press that if such an accident had taken place
after the separation of the LC from the MM, then the astronauts would
have inevitably died.
_ BIBLIOGRAPHY
- AERONAUTICS AND SPACE REPORT, AEROSPACE DAILY, AVIATION WEEK AND SPACE
TECHNOLOGY, ELECTRONICS NEWS, INTERAVIA AIR LETTER, NASA NE14S RELEASE,
SCIENCE NEWS, SKY AND TELESCOPE, SPACEWARN BiJLLETIN, SPAC E WORLD
- COPYRIGHT: IZDATEL'STVO "SOVETSKAYA ENTSIKLOPEDIYA", 1971
- 48
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OI'FICTAL USE ONLY
SOVIET SPACE RESEARCcI IN 1971
Moscow YEZHEGODNIK BOL'SHOY SOVETSKOY ENTSIKLOPFDII in Russian No 16, 1972
pp 509-519
[Article by L. Lebedev]
_ [Text] The "Salyut" orbital scientific station, the "Soyuz-10" and "Soyuz-
- 11" manned transport ships, and automa.tic stations for studying the moon
and Mars were launched in 1971. The launchings of artificial earth satel-
- lites for purely scientific and applied purposes have continued.
- The "Salyut" permanent orbital scientific station is a complex new type of
manned spacecraft designed to perform broad scientific and technical research
and experiments in near-earth space. The "Salyut" station (see Figures 1
and 2) has three basic compartments: the transfer compartment (TC), the
working compartment (WC) and the equipment bay.
The transfer compartment is one of the work facilities of the station. The
hull of the TC is sealed. Elements of the life-support and heat regulating
systems, the equipment of the "Orion" astrophysics observatory and the con-
- trol panels are installed inside this compartment. Outside there are two
- solar cell panels, the search and guidance system antennas, light indicators
- which are switched on during final approach and docking, ion sensors, an
outside scanning television camera, the heat regulating system units, round
- compressed gas tanks, and the telescope of the "Orion" observatory. The
TC includes the assembly for docking the station with the "Soyuz" spacecraft
in earth orbit. The TC is connected to the WC by a hatchway equipped with
automatic and manual drives.
The working compartment is the basic working and living facility of the sta-
- tion. Structurally this part of the "Salyut" station is in the form of two
_ cylinders 2.9 meters and 4.15 meters in diameter joined together by a conical
cowling. The WC is also sealed. The equipment of the life support system,
the radiotechnical and televis: n equipment, the control equipment for*the
_ onboard complex, the power supp._j, orientation and control of motion, tele-
metry, crew panels and work spaces, interior parts, devices to aid the crew
49
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
= in moving about and staying in place, scientific and experimental equipment
~ an:l the food and water reserves are inside the WC. The radiator panels of
the heat regulating system, the antennas of the communications systems and
radiotelemetry, sun sensors and viewers are installed on the outer surface
= of the WC. A gas composition similar to the atmosphere on the surface of
the earth and also the required temperature and humidity are maintained in
the living quarters of the station. In order to work with the orientation
and navigation devices, take photographs and make visual observations, the
transfer and working compartments of the "Salyut" have 24 windows with re-
placeable or fixed equipment.
An unsealed equipment bay is located in the end section of the WC hull in
which there is a concentration of equipment which provides for the control
oF the movements of the station--maneuvering to change the orbital parameters
or orientation of the station in space. For this purpose, a multiple-use
= correction engine and fuel tanks are installed under the shielding in the
_ equipment bay. The engines of the orientation stabilization system with
- fuel tanks and round compressed gas tanks (compressed gas is used as the
. working medium of the actuating elements) are placed on the hull of the
equipment bay. The antennas of the radio communications and radio monitor-
ing systems, lights, and heat regulating system units, ion sensors, outside
- scanning television camera, the solar cell panels and the search system an-
_ tennas are placed on the hull of the equipment bay.
The power supply for the onboard equipment comes from a single power system
. which includes solar cells and chemical current sources. The panels with
the solar elements are 42 m2 in area.
The crew is delivered onboard the "Salyut" station by the "Soyuz" transport
spacecraft. In connection with the performance of new functions, certain
- systems and devices of the spacecraft have been modified. In particular,
- a new structural design has been developed for the docking assembly. Its
_ component elements--a docking pin and receiving cone--are installed on the
_ hatch covers of the "Soyuz" spacecraft and the "Salyut" station, which open
inward. After docking the spacecraft to the station, the units are rigidly
- joined mechanically, and their electric circuits and hydraulic lines are con-
_ nected. A sealed tunnel is formed between the "Soyuz" and the "Salyut"
_ which permits the cosmonauts to move from the "Soyuz" to board the "Salyut."
- After completion of the flight program, the crew returns to the "Soyuz," un-
� docks the spacecraft and then returns to earth.
_ The "Salyut"-"Soyuz" space complex is 21.4 meters long. Its maximum diame-
ter is 4.15 meters, and the sealed compartments are approximately 100 m3 in
size. The orbital complex weighs more than 25 tons. The "Salyut" station
= weighs 18,900 kg.
= The "Salyut" scientific station was launched on 19 April. The orbit was
- corrected on the same day. Four days later, on 23 April at 0254 hours*,
* rioscow time is used here and hereafter.
50
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
- FOR OFFICIAT. USE ONLY
the "Soyuz-10" spacecraft was launched, and at 0303 hours, it was inserted
_ into the calculated orbit. The crew made up of the spacecraft commander
- V. A. Shata.lov, fli~ht engineer A. S. Yeliseyev and test engineer N. N.
Rukavishnikov were onboard.
During the joint flight of the "Salyut" and "Soyuz-10" a number of studies
were made to check out the fitness of the improved systems, providing for
~ mutual search, long-range approach, fi.nal approach, dccking and undocking
- of the spacecraft and the station. On 23 April, at 1315 hours, a correction
- was made to the "Soyuz-10" orbit. As ,3 result of the correction, the dis-
tance between the vehicles decreased to several kilometers on the morning
_ of the 24th of April. This made it possible to put the automatic rendezvous
- system into operation. In the given experiment the "Soyuz-10" was the "ac-
- tive" spacecraft and completed all of the maneuvers of rendezvous with the
"Salyut" station. When the distance between the vehicles was reduced to 180
- meters, the crew switched to manual control and docked the "Soyuz-10" with
- ttie "Salyut" station. The rendezvous, final approach and docking system and
- also the equipment used was developed earlier in the experiments with the
~ "Cosmos" series of satellites and in the previous flights of the "Soyuz"
- transport ships. The basic difference of the operations on the given flight
- was that two space vehicles with significantly different masses were docked
for the first time. The processes of maneuvering in direct proximity and
docking, the control of the "station transport ship" space system are very
different from the point of view of flight dynamics from experiments in which
such operations are performed by like units as was the case earlier. There-
fore the enormous practical experience abtained in docking the different type
"Soyuz-10" and "Salyut" spacecraft, difrering with respect to mass and geo-
metric dimensions, was very usefLl to the future development of orbital
stations.
The flight of the "Salyut"-"Soyuz-10" space system lasted 5 hours 30 minutes.
During the flight the onboard systems were tested, and the dynamic charac-
. teristics were evaluated. After performance of the planned experiments, the
- crew undocked and separated the spacecraft from the station. Then the cosmo-
nauts circled the "Salyut" duz�ing which time they examined and photographed
the station from different sides. Then the vehicles drew apart and continued
~ their joint flight, proceeding further with the program of scientific and
~ technical experiments.
The flight of the "Soyuz-10" transport ship ended on 25 April: at 0159 hours
- it withdrew from its orbit and at 0240 hours it made a soft landing at 120
km northwest of Karaganda. The studies made during the flight of the "Soyuz-
' 10" were the first phase of the joint program of operations with the "Salyut"
- orbital scientific station. Its flight continued. The variation of the
- orbital parameters of the "Saly,it" du..ing the period from 30 April to 15 May
" is presented in Table 1.
- � The second phase of the space experiment began with launching the "Soyuz-11"
transport ship on 6 June at 0755 hours. The "Soyuz-11" transport ship was
inserted in earth orbit at 0804 hours. It was piloted by the crew made up
51
_ FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
- the ship commander G. T. Dobrovol'skiy, the flight engineer V. N. Volkov and
test engineer V. I. Patsayev. At 1350 hours, a correction was made to the
orbit using manual orientation. The "Soyuz-11" transport ship completed its
Plight at altitudes of 185 to 217 km with an orbital period around the earth
= of 88.3 minutes. On the morning of 7 June, the operation of rendezvous and
_ docking in orbit of the "Soyuz-11" with the "Salyut" station was started.
- Table
Orbital parameters
30 April 1971
7 May 1971
15 May 1971
� Apogee (km)
277
269
260
Perigee (km)
251
249
242
= Inclination (deg)
51.6
51.6
51.6
= Orbital period (min)
89.6
89.6
89.0
The docking process was carried out in two steps. Initially the automatic
= control system brought the units to a distance of 100 meters from each other.
The final approach was made by the crew of the "Soyuz-11". After the final
= approach of the "Soyuz-11" to the "Salyut", rigid mechanical docking of the
= spacecraft was carried out, and their electrical circuits and hydraulic com-
= munications were connected up. Then the astronauts checked the seal of the
_ compartment and the operation of the onboard systems of the stations, the
= parameters of the microclimate. They opened the covers of the sealed hatch
~ connecting the ship to the station. At 1045 hours, they entered the "Salyut"
station and proceeded with the further flight program. The en.gineering-tech-
- nical problem of delivering a crew by a transport ship onboard a scientific
' satellite station of the earth was solved for the first time. The first
manned orbital scientific station in the world began functioning. Its orbi-
tal parameters at the beginning of the flight and after two corrections are
- presented in Table 2.
_ Table 2
7 June 1971 8 June 1971 9 June 1971
Orbital parameters at beginning after first after second
- of flight correction correction
Apogee (km)
240
265
282
Perigee (km)
212
239
259
IncZination (deg)
51.6
51.6
51.6
Orbital period (minutes)
88.2
89
89.7
An important role in the experimenta.l program onboard "Salyut" was played
- by the medical-biological research. It made up a significant part of tha
program on the 4th, 6th and 7th work days of the crew. They were also per-
- formed on other days. The purpose of the medical experiments was to monitor
52
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFF'ICIAL U5E ONLY
ttic state of health of the cosmonauts and to perform a basic study of the -
human or.ganism for scientific forecasting of thc reaction of varj.ous systems
of the organism to the effect of the spaceflight factors. New specialized .
- onboard clinical equipment was used for medical-physiological mensurement.
An especially deep study was made of the reaction of the cardiovascular sys- -
rem to weightlessness. The application of multichannel amplifying and con- .
- version units and specializecl medical equipment made it possible to obtain -
complex multilevel information about the activity of the vitally important
systems of man, and primarily, the cardiovascular and respiratory systems. -
_ SigniFicantly more parameters than before were monitored on the station crew: -
- the volume and rate of inhalation and exhalation, arterial pressure, the
- propagation rate of the pulse wave through the arteries, and so on. The =
device made it possible to determine the phases of the cardiac cycle and
measure the pulse of the femoral artery, to record 12 electrocardiograms and _
about 30 circulatory parameters. Blood was taken from all members of the
- crew for laboratory testing on the ground. In order to esimate the effect
- of the conditions of weightlessness on the changes in the human organisms
during f.light, measurements were made of the bone tissue density. Studies -
- were performed oF the visual characteristics of eyes, and the strength of -
the hands was measured. -
The cosmonauts regularly performed physical exercises. They trained on a -
"treadmill" permitting the walking skills and muscle strength to be main-
~ tained in weightlessness. They useu,special suits which "loaded" the skele- -
- tal and musciilar system. Thus, a number of ineasures were taken which were ~
intended to some degree to compensate for the absence of the customary grav- -
- ity.
Onboard the "Salyut", an experiment was performed with respect to studying -
- the effect of the conditions of weightlessness on frog er.ibryos and the de-
= velopment of certain types of higher plants. -
An important contribution to the various branches of science and the national.
_ economy was made by the results of the experiments in studying earth and the
- atmosphere from space which the crew performed using the station equipment.
. One of the problems, the solution of which was worked on successfulZy by
= Soviet science and cosmonauts was the study of the optical characteristics
= of the day, night and twilight horizons of the earth. The crew of the "Sal-
_ yut" also made spectrographic recordings of individual sections of the earth's
surface in order to develop a procedure for distinguishing natural formations
by the peculiarities of the reflection spectra characteristic of them. Seri-
ous attention was given to the problem of the effect of the layers of the
atmosphere on the reflected radiation spectrum. The complex geophysical
experiment was realized for these purposes. During the ninth working day
_ the station crew made a spectral survey of the characteristic formations of
_ the earth's surface and the coi tal regions of the Caspian Sea. Simultane-
- ously, an aerial photographic survey was made of the same regions from spe-
- cially equipped aircraft of the Leningrad State University and USSR Academy
of Sciences Expedition.
- 53 -
_ FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
The cosmonauts constantly made observations and photographs of the various
atmospheric formations and phenomena (typhoons, cyclines, and so on), the -
- cloud cover and the characteristic sections of the earth's surface from the
" geological point of view. They also photographed the cloud cover above -
_ par.ts of Povolzh'ye. Simultaneously, the television survey was made of the
_ same cloud formations by the "Meteor" satellite. The purpose of this ex-
periment was to study the fine structure of the cloud systems and develop -
_ a procedure for decoding the television photographs received from the "Meteor"
_ satellite. -
The experiments with respect to studying the primary cosmic gamma radiation -
_ which were performed by the crew of the "Salyut" using a gamma telescope and
- also the astronomical observations using the orbital "Orion" observatory have -
- important significance. During the flight of the "Salyut" station, spectro- _
- grams were made of the stars Beta Centauri and Alpha Lyra in the wavelength
range of 2000 to 3800 angstroms. The work with the "Orion" system confirms -
the correctness of the basic principles of the creation of observatories be- _
yong the atmosphere operating under the conditions of outer space and con-
_ trolled by an astronaut inside an orbital station, used as the basis for its -
development. The crew of the "Salyut" also performed purely technical ex-
periments connected with the testing and development of new instruments and
space engineering units under actual conditions of orbital flight. The -
- cosmonauts performed studies of the wide-angle viewer--a new device for exact -
- orientation on the sun and planets. They performed multiple navigational
- measurements and used the onboard, computer to determine the orbital parameters
of the station. The new ion orientation equipment was checked out, the ac-
- curacy of the operation of the gyroscopic device was investigated, a study -
- was made of the effect of the space environment on the optical surfaces of
= the ports and on the properties"of special optical specimens investigated
to develop astronomical instruments for use beyond the atmosphere. New ele- -
- ments of life support systems designed for long-range flights were tested. -
- By using the multifunctional "Era" equipment a study was made of the phe-
_ nomenon of high-frequency reson~ance on the transmitting radio antennas. The �
parameters of the ionosphere were measured, and a study was made of the spa-
tial distribution of the charged particles near the station. The potential
- of its hull was determined. Other processes and phenomena were investigated -
which accompanied the movement of the station in a rarefied low-temperature
plasma. The cosmonauts performed experiments to measure the levels and tis- -
sue dosages of radiation which is important for an effective dosimetric moni- .
toring system. Observations ware made of the micrometeor situation in outer -
space. ~ -
The development of autonomous means and methods of orientation and naviga-
- tion and also the control system for the "Salyut"-"Soyuz" complex during
, maneuvering demonstrated the good controllability of the new space system
and eEfectiveness of the manual control and orientation.
- .54
- FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
- FOR OFrICIAL U5E ONLY
'I'he flight of the "Salyut" station with the crew onboard lasted 23 days.
'Che cosmonauts completely carried out the program of scientific and tech-
nical experiments and on 29 June, after transferring the research material
from the flight logs to the "Soyuz-11" ship, they took up their work places
in its cabin. At 2128 hours, the "Soyuz-11" spacecraft and the "Salyut" sta-
- tions undocked and continued further flight separately. In order to realize
- the reentry to earth, on 30 June at 0135 hours the braking engine of the _
- "Soyuz-11" was switched on, and operated for the calculated time. In ac-
� corc?;znce with the program, after aerodynamic braking in the atmosphere, a -
parachute system operated and the soft landing engines were engaged directly before the earth.
The flight of the reentry vehicle ended in a smooth landing in the given
- area, but 30 minutes before landing rapid decompression of the cabin took _
- place which killed the cosmonauts.
'rlle spaceflight around the earth of G. T. Dobrovol'skiy, V. N. Volkov and
- V. I. Patsayev made an invaluable contribution to the development of cosmo-
_ nauts. It offers the possibility of going ahead along the path of utiliz-
ing long-term manned orbital stations, opening up the road for new accomplish- ments. The unprecidented feat of the heroes will always remain in the his- -
tory of the conquering of outer space. _
From 29 June to 11 October the "Salyut" station functioned in earth orbit _
automatically. On 20 July the orbital parameters had the following values:
apogee 262 km, perigee 223 km, orbital period 89.25 min, inclination 51.6�.
On 11 October, the final operations were performed from the "Salyut" station
to bring it out of artificial earth orbit. After orientation of the "Salyut"
in space, the braking was switched on. As a result of its operation, the -
- station went into the reentry trajectory; it entered the dense layers of the atmosphere above the given part of the Pacific Ocean and ceased to exist. _
. Altogether, the "Salyut" station remained under the severe conditions of
outer space for almost six months, and for all of this time the systems which =
provided for its functioning both in the manned and in the automatic modes
- operated continuously.
In 1971, the automatic self-propelled "Lunokhod-1" delivered to the surface
of the moon on 17 November 1970, was still functioning (see YEZHEGODNIK BSE
- [Great Soviet Encyclopedia Yearbook], 1971). At night on 8 January, the
communications sessions held with the "Lunokhod-1" and the program of the =
third lunar day was started. One of the basic problems of this period was
getting the lunokhod to the location with given selenographic coordinates-- -
- the landing site of the "Luna-17" automatic station. It was necessary to -
estimate the accuracy and reliability of the navigation system and check
_ the methods of navigation, remote cont::ol and guidance of the lunokhod. The
self-propelled unit moved towark the landing stage over a new path (Figure
. 4). The general direction of motion was to the norttiwest. The current co-
- ordinates of the unit were determined using onboard navigational devices and
_ they were periodically corrected with respect to the position of the sun
- and the earth. This provided for getting the unit to the calculated point =
55
FOR OFFICIAL USE ONLY -
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFTCIAL U5E ONLY
~
Figure 2. lliagram of the "Salyut" orbital station: 1--orbital compartment
o� the "Soyuz" transport ship; 2--lights; 3--scanning antenna of the search
system; 4--television camera; 5--guidance system antenna; 6--docking pin;
7--receiving cone of the docking unit; 8--solar cell panels; 9--equipment
oE the "Urion" astrophysical observatory; 10--hatchway; 11--light indexes;
12--scientific equipment of the working compartment; 13--domestic equipment;
14--microengines of the orientation system; 15--unit compartment system;
16--cosmonaut's chair at the station control panel; 17--compressed gas
bottles; 18--orientation sensor.
Eigure 3. Fragment of the orbital panorama with image of the vicinity
of Sinus Aestum of Oceanus Procelarum with the Eratosthenes crater
56
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
I'UR OrFICIAL USE ONLY
at t]Ze given time. During the third lunar day it traveled a path 1936 -
me.ters long. On arrival of the lunar night on 21 January, the lunokhod -
was again in the stationary position, and on 7 February it began to move -
= to the north, in the direction of Cape Heraclide (Figure 5). By 19 Febru-
ary, the planned three-month program of scientific and technical research
anci experiments was completed. In four lunar days the self-propelled -
laboratory had Craveled 5228 meters. The analysis of the condition and
the operation of the onboard systems demonstrated the possibility of con- -
tinuing active functioning of the automaCic unit on the lunar surface.
= For this purpose, an additional lunokhod work program was compiled. The -
successful functioning of the spacecraft continued 10.5 months and ceased _
on 4 October. The cessation of the active operation of the "Lunokhod-1"
- was caused by the burnup of its isotopic heat source, which led to a drop _
in temperature inside the unit during the eleventh lunar night from 15 to -
30 September. ~
Figure l. "b11yllL" OTD1L11 SL3L1on: l-- JVyLLG LL"d11.51JVLL ship,
Il--transfer compartment; III--working compartment; IV--unit compartment.
During the scientific research and the design engineering testing, the self-
propelled automatic vehicle traveled a distance equal to 10,540 meters, which
_ made it ~ossible to examine the lunar surface in detail over an area of
_ 80,000 m. For this purpose, using the vehicle's television system, more than
- 200 panoramas and more than 2,000 pictures of the lunar landscape were ob-
tained. Moreover, at 500 points along the route a study was made of the
physical-mechanizal properties of the surface layer of the ground, and at
25 points an analysis was made of its chemical composition.
= While examining the landing area of the "Luna-17" automatic stations, the
following were constructed: a topographic diagram of the route on a 1:1000
- scale, a more precisely defined schematics of the individual sections on a
1:200 scale, topographic plans of the individual sections on a 1:100 scale
- obtained by the stereophotograi ietric method and altitude profiles of the
route and characteristic crateri.
57
= FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
,
- The geological-morphological description of the area was made studying the _
- panorama images using the topographic characteristics of the terrain, data ,
- on variations in the physico-mechanical and chemical properties of the soil
- and the positions of the vehicle along the path. The geological-morphologi- ,
cal. schematics of the areas where "Lunokhod-1" stopped were obtained, and a
number of conclusions were drawn on peculiarities of the study area. The -
landing site of the "Luna-17" automatic station and the work area of the
"Lunokhod-1" are a slightly undulating plain, on the surface of which there
- are cuplike craters, some more defined than others. This plain is made up =
~ of basaltoid rock and probably was formed by areal eruptions of lava. The -
- rock was covered by a thin lower of regolith. With respect to general mor-
phology, the nature of the regolith and the spread of the craters and rock,
~ the investigated region is similar to the previously studied marine areas of
the equatorial zone of the moon. This indicates the generality of the laws _
- oF formation and evolution of the lunar surface over the significant areas
of the lunar seas. It was established that among the small craters (from 5-
10 cm to 30-40 meters) the craters with smooth shapes predominate, and the
number of fresh craters with even forms of relief amounts to no more than _
- a few percentages of the total of all of the craters. This indicates that
the process of formation of the craters on the surface of the moon extended _
over a long period of time, and the form of them varies with age--their out- _
lines become smoother and softer. :
a.
b.
c.
d.
e.
f.

h.
Figure 4. Topographic schematic of the path of the "Lunokhod-1" from
- 17 November 1970 to 1 January 1971.
[Key on follawing page]
- 58
- FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
I
FOR OFFICIAL USE ONLY
[Key to Figure 4 on previous page]
- a. landing site of the "Luna-17" e. rock placers
automatic station f. craters and holes
b. path of movement of "Lunokhod-1" g. central hil's
- c. studies of the chemical composi- h. direction of motion
-i tion of the lunar soil
~ d. individual rocks
On the panoramas, many rocks are visible with a cross section from 1-2 cm
to 40-50 cm. The presence of the basic part of the rocks on the surface of
tite moon is connected with ejection of them from craters. Inasmuch as the
number of rocks increases sharply near the large craters, it is possible to
assume that these craters penetrate across the regolith to the rocky base.
a.
b.
c.
d.
e.
f.
Figure 5.
Topographic schematic of the
path
of "Lunokhod-1" from
7 F'ebruary
1971 to 13 April 1971
Key: a.
path of the "Lunokhod-1"
d,
rock placers
b.
studies of the chemi-31 com-
e.
craters and holes
position of the lun~~ soil
f.
direction of motion
c.
individual rocks
59
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
- FOR OFFICIAL USE ONLY
The rocks in the material ejected from the fresh craters are quite varied =
with respect to shape. This obviously is connected with certain differences '
in the petrographic composition of the rock in the foundation. The rounded
rock is basically encountered near the mature craters which can be inter- ,
preted as the result of the general direction of evolution of rock as a func- ~
tion of exposure time on the surface of the moon under the effect of exogenic -
factors.
The regolith which covers the surface of the rock is the weakly connected
material of different grain size significantly less than 1 mm containing a - noticeable amount of debris and different sized rock. This material is to -
a significant degree elastic, formed by crushing of the lower-lying rock. -
- The rockiness of the regolith is different and most expressed in the struc-
= ture ~~f the crater swells. The thickness of the regolith varies sharply in
the investigated area, and its fluctuations are within the limits from 1 to _
5 meters. The surface evolution takes place under the predominant effect ~ of two factors: 1) the formation of the impact-explosive and impact craters
- with sharp, even shapes accompanied by ejection of rock and 2) destruction _
of the craters occurring at different times accompanied by the surface ero- -
sion and destruction of the rock. '
An express analysis of the chemical composition of the lunar soil along the -
- path of the "Lunokhod-1" was made using the spectrometric equipment. During _
its functioning, the special isotopic source irradiated the investigated -
section of the lunar surface with x-rays, ionizing the atoms of different
elements which enter into the composition of the lunar soil. Here recipro- .
cal x-radiation occurred, the energy of which strictly corresponds to cer-
~ tain chemical elements. The recording of the reciprocal radiation and -
= measurement of its energy made it possible to determine which elements were
subjected to irradiation and what their content in the soil was. The chemi- _
cal composition of the lunar soil was investigated at many locations with _
characteristic geological and morphological features. A study was made of
- the undisturbed surface, the craters of different ages (including the in-
dividual parts of the craters: bottom, slopes, swells), the rock lying at
a depth of about 10 cm which was denuded during the special maneuvers of the
lunokhod and also individual rocks. In addition, a complex study was made
~ of a number of sections of the lunar surface: both the physical-mechanical
- and the chemical composition were determined in the same section. As a re- _
- sult of the studies of the chemical composition, variations in the aluminum,
calcium, silicon, iron, titanium, and other element contents were determined. '
The data obtained confirm the general idea of the origin of the regolith as -
= a result of crushing of the rock of basically basalt composition. _
The physical-mechanical properties of the lunar soil were determined by
several methods: the introduction of a conical-vane stamp into the soil
with subsequent rotation, measurement of the interaction of the "Lunokhod-1"
_ wheels with the soil and analysis of the images of its tracks. The use of
several procedures simultaneously to obtain the information made it pos--
sible to determine the properties of the lunar soil in sufficient detail.
60
~ FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OrFICIAL USE OM,Y
Along ttie entire path of the lunoktiod, the soil is fine-grain material hav-
_ ing noticeable forces of adhesion. With respect to granulometric composi-
tion and behavioral peculiarities, tilere are no signi�icant differences
= from the soil at the landing sites of the other spacecraft, including the
"Luna-16" automatic station (see YEZHEGODNIK BSE [Great Soviet Encyclopedia
Yearbook], 1971). The fine-grained layer of soil basically has a depth of
no less than 50-100 mm and is quite uniform with respect to depth. The
- uppermost layer of the soil is loose, powdery, easily deformed material.
- The bearing capacity of the soil determined by introducing a stamp is within
the limits of 0.2 to 1.0 kg/cm2, the resistance to rotational shear is from
- 0.02 to 0.09 kg/cm2. The most widespread value of the bearing capacity was
0.34 kg/cm2 and the most widespread resistance to rotational shear was
0.048 kg/cm2. The indexes of the mechanical properties of the soil increase
= with depth. With repeated impressions by the die, good compacting of the
- upper layer took place with an increase in bearing capacity. The mechani-
- cal properties of the various lunar formations vary within broad limits.
. Along with the quite firm rock, lumps are encountered which are made up
of conglomerate material and have low strength.
- The scientific equipment For studying cosmic radiation of solar and galac-
tic origin, monitoring of the radiation situation on the fly-by trajectory
~ of the "Luna-17" station and recording the radioactivity on the lunar sur-
= face during the operations of the self-propelled unit was adjusted to re-
- cord protons, electrons and alphaparticles of differe:it energy primarily in
_ the energy ranges inaccessible for study from the earth as a result of the
- shielding effect of its atmosphere. Part of the calendars were placed at
different angles to the axis of the lunokhod which permitted not only meas-
- urement of the intensity of the particle flux but determination of their
energy spectrum, and estimation of the composition of the cosmic rays, but
_ also discovery of the nature of the angular distribution of the fluxes, that
is, the direction of approach of the particles to the moon.
On the flight trajectory to the moon, radiometric pquipment recorded the _
proton flux with an energy of 1 to 5 Mev from the very beginning of the -
flight of the "Luna-17" automatic station which exceeded by two orders the
_ background particle flux in interplanetary space. During the four days of
flight to the moon, the intensity dropped by approximately 5 times. At the
same time, a slow restoration of intensity of the galactic cosmic radiation =
- was recorded. The subsequent analysis calling on the solar data and data on -
the intensity of the protons of the same energy obtained by the analogous
equipment on the "Venera-7" automatic station (see YEZHEGODNIK BSE [Great
Soviet Encyclopedia Yearbook], 1971) demonstrated that the last phase of
the drop in intensity of the large buildup of solar protons caused by the -
powerful proton solar flare occurring on 5 November 1970 was recorded. -
- After the landing of the "Luna-17" at~omatic station on the surface of the `
_ moon, the intensity of the gal ztic cosmic radiation was approximate'ly cut _
in half by comparison with the level recorded during the flight time. This =
- indicates shielding of the radiometer from the isotopic flux of galactic
61
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
cosmic radiation by the body of the moon and confirms the conclusions of
low radioactivity of the surface layer of the moon previously drawn as a
result of the flights of the "Luna" series of automatic stations. During
the first lunar day on the surface of the moon from 17 to 20 November 1970,
a buildup in intensity by three times from the level of significant (just
= as in the fly-by section) background was recorded, which was connected with
the solar flares occurring during this period. On 12 December 1970, a sig-
~ nificant buildup of intensity of the protons with an energy of 1-5 Mev be-
gan. On 13 December it reached a maximum, exceeding the background level
' by approximately 104 times. The intensity at the maximum was 1.3�103
cm 2�sec-1'ster 1 for protons with an energy of 1-5 Mev. At the end of
the day of 14 December, the intensity diminished sharply by approximately
two orders, after which it decreased slowly for the next 8 days. The build-
_ up in intensity of the solar cosmic radiation was caused by a series of flares
occurring on the sun on 10 and 11 December. The previously obtained data
and the results of the studies of the cosmic radiation using the "Venera-7"
- and "Lunokhod-1" automatic stations indicate that the proton activity of the
- sun had decreased slowly from its maximum in 1968-1969. A sharper decrease
in proton activity was observed in the second half of December 1970.
: The x-ray telescope installed on the "Lunokhod-1" made it possible to study
the cosmic x-radiation background and the discrete x-ray sources. It in-
_ cludedptwo proportional x-ray proton counters for the spectral range of 2
_ to 10 A. Collimators were installed in front of the counters to limit the
field of view of each counter to a cone with an aperture angle of about 3.5�.
The axes of the counters were directed to the local zenith with the lunokhod
in the horizontal position. A filter which was opaque for the investigated
- range of x-radiation was placed in front of the entrance opening of one of
the counters. As a result, one of the counters recarded the cosmic x-radia-
tion together with the background of cosmic particles, and the other counter,
only the particle background, and it was the control. On rotation of the
= moon around its axis, the field of view of a telescope slid along the celes-
tial sphere. In 18 to 20 hours the telescope rotated by 9 to 10�. Observa-
tions were ma.de of the x-radiation with the lunokhod at the halt. One ex-
- posure time was 6 hours. As a result a strip on the celestial sphere inter-
- secting the plane of the galasy in the vicinity of the constellation Cygnus
_ was scanned. The results of the measurements of the x-ray background agree
well with the preceeding data. The contribution of the galaxy to the x-ray
background is very small. Discrete x-ray sources were observed.
The device for laser ranging of the moon manufactured in France and instal-
led on the "Lunokhod-1" is a special Iight reflector made up of 14 three-
sided prisms with the side of one face equal to 10 cm. The right angles
between faces were maintained with a precision to tenths of angular seconds.
The successful experiments performed in the Soviet Union and in French made
- it possible to obtain independent high-precision measurements of the parame-
. ters of the earth-moon system: in the first experiments the distance to the
laser reflector was measured with an error not exceeding + 3 meters.
- 62
- FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
rOR OFFICIAL USE ONLY
_ 'Itie booster rocket wiCh the "Luna-18" automatic station onboard was launched
_ on 2 September. The station was launched toward tlie moon from earth orbit.
' During the course of the fli.ght on 4 and 6 September, corrections were made
to Lile trajectory. On 7 September on approaching the moon, the station was
- braked, as a result of which it went into a circular selenocentric orbit
=i with the following parameters: altitude above the lunar surface 100 km,
incLination of orbit to the plane of the lunar equator 35�, orbital period
around the moon 1 hour 59 minutes. On flight along the selenocentric orbit
the station maneuvered in order to work out the methods of automatic near-
lunar navigation and land on the surface of the moon. The braking engine
- was started on 11 September, the station left its orbit and reached the
surface of the moon in the vicinity of the continent surrounding the Mare
~ Foecunditatls at the point with the coordinate 3�34' north latitude and
56�30' east longitude. The landing area was selected in a mountainous area
which is of great scientific interest. However, as the measurements demon-
~ strated, the approach of the station to the moon under these complex topo-
graphic conditions turned out to be unfavorable.
~ On 28 SeptemUer, the "Luna-19" automatic station was launched. The basic
i purpose of the experiment was to perform scientific studies of the moon
and lunar space from the orbit of an artificial lunar satellite. The sta-
- tion was sent to the moon from earth orbit. On 29 September and 1 October,
corrections were made to the trajectory. On 3 October, as a result of a
braking maneuver, the "Luna-19" automatic station went into circular seleno-
centric orbit caith the following parameters: altitude above the surface of
- the moon 140 km, inclination of the orbit 40�35', orbital period 2 hours 01
. minutes 45 seconds. As a result of a correction on 6 October, the orbital
- parameters became: aposelene 135 km, periselene 127 km, orbital period
. 2 tiours 01 minute. On 26 and 28 November two more corrections were made to
the station orbit. The orbital parameters began to have the following
- values: aposelene 385 km, periselene 77 km, inclination 40�41', orbital
period 2 hours 11 minutes. The "Luna-19" automatic station conducted studies
for many months in selenocentric orbit. By the results of the radiotechni-
cal measurements of the orbital parameters, studies were made of the gravi-
tational field of the moon by the method of systematic prolonged observa-
- tions of the evolution of the orbit. Continuous measurements of the charac-
teristics of the interplanetary magnetic field in the vicinity of the moon
were made from onboard the station. It was recorded that the field from the
illuminated side of the moon is several times stronger than the undisturbed
interplanetary magnetic field. At the same time, on the night side the mag-
, netic field is noticeably attenuated. Both of the indicated experiments
were performed for more precise determination of the scientific concepts of
_ the internal structure of the moon. By using the "Luna-19", the stuay of
the characteristics of cosmic radiation in lunar space were continued.
. Simultaneously, analogous meaF-~rementa were made by the equipment onboard
_ the "Mars-2" and "Mars-3" stat :)ns. As a result, interesting, valuable
scientific information was obtained on the dynamics of the variation in
intensity of the corpuscular fluxes of cosmic radiation. Along with the
_ studies indicated, the density of the meteor flux in lunar space was meas-
ured. The scientific research program of the "Luna-19" automatic station
63
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
= also included a survey of individual areas of the lunar surface. For this
_ purpose, two optico-mechanical television cameras were installed on the sta-
tion. Their characteristic feature was that the scanning of the image along
the flight line was realized as the result of the orbital motion of the sta-
- tion itself.
Figure 3 shows a fragment of one of the orbital television panoramas. The
_ large structural shapes of the lunar relief are clearly isolated on the pano-
ramas: the seas, continents, craters and faults. Therefore they can be
_ used to study the shapes of the basic geological structures, the degree of
_ their destruction and the general nature of the relief and to gather the
information required to reconstruct the history of the moun.
' On 19 and 28 May, the "Mars-2" and the "Mars-3" automatic stations were
launched toward the planet Mars (see Figure 9).
= On 27 November, the "Mars-2" automatic station for the first time delivered
- to Mars a capsule inside which a USSR flag was included. On 2 December, for
_ the first time in history the reentry vehicle of the 11Mars-3" automatic sta-
tion made a soft landing on the surface of Mars. The "Mars-2" and "Mars-3"
stations became artificial satellites of the planet.
The "Mars-3" automatic station (see Figure 6) includes an orbital station and
_ a reentry vehicle and is equipped with systems for autonomous control and
orientation, radio control, trajectory measurements and data transmission,
automation, power supply, heat regulation, onboard radio, a program and
_ timing device, an engine and a set of scientific equipment. The "Mars-2"
= and the "Mars-3" automatic stations are similar with respect to structural
= design. The weight of each station was 4,650 kg. Structurally the orbital
_ station is made up of the following basic parts: the instrument compartment
(IC), the tank module (TM), the engine (EN) with the automation components,
the solar cell, the antenna-feeder unit, and the heat regulating system
regulators. The onboard systems of the station are located in the IC. The
- optoelectronic instruments of the system for astroorientation on the sun,
the earth and a star and the autonomous navigation system and scientific
= equipment are located outside. The IC is connected to the TM which serves
as the basic support element of the station. The EN is located in the lower
part of the TM. Above, there is an adapter for attaching the reentry vehicle.
The panels of the solar cell, parabolic and low directional antennas are
= mounted on the TM. The radiators of the heat control system are attached to
one of the panel suspension beams. Part of the scientific equipment, two
antennas for radio communications between the orbital station and the re-
entry vehicle, the antenna for the Soviet-French Stereo experiment and the
microengines of the orientation stabilization system are installed on the
solar cell panels.
64
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
Figure o. "Mars-3" automatic station: 1--instrument compartment; 2--antenna
of the Stereo scientific equipment; 3--unidirectional parabolic antenna;
4--ree:ztry vehicle; 5--radiations of the heat regulation system; 6--solar
cell panel; 7--engine tank module; 8--optoelectronic devices of the astro-
orientation system; 9--antennas for communications with the reentry vehicle;
10--magnetometer; 11--low-directional antennas; 12--optoelectronic device
of the autonomous navigation system; 13--correcting and braking engine
Key: a. view A
The reentry vehicle (see Figu a 7) consists of the automated martian sta-
tion (AMS), the instrument-parachute container, the braking shield and con-
_ necting frame. On the frame there is a solid-fuel engine for conversion of
- the reentry vehicle from a flight trajectory to landing trajectory and the
- 65
- FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY -
- components of the autonomous control system for stabilizing the reentry ve- ~
liicle after separation from the orbital station. The instrument-parachute
container is made in the form of a torus. It is installed on the surface
= of the automatic martian station and is joined to it by means of straps.
Tlie pilot and matn parachutes are placed inside the container. The con- -
tainer has a powder engine for releasing the pilot parachute, a soft land- _
, ing braking engine and a parachute discharge engine, the antenna of the radio -
. altimeter, the antenna for communications with the orbital station and scien-
- tific equipment. The cone-shaped braking shield is used for aerodynamic -
braking of the reentry vehicle in the martian atmosphere and shie"lding it -
from the high temperatures occurring in this case.
Inside the automated martian station there is a sealed instrument compart- -
ment. It has the equipment for the autonomous control system, the radio ~
_ complex and telemetry, the scientific instrument modules, including the
tel.evision panorama head. Outside are the scientific instruments with the
= mechanisms for remote use of them, the radio complex antennas, the antennas -
- for putting the station into operation after landing. The required operating =
sequence of the systems is insured by the program-timing device. The heat -
control system for the reentry vehicle of the "Mars-3" station included
vacuum-shielded heat insulation, radiation and electric heaters. _
The control system included an orientation system, a gyroscopic unit provid-
= ing for stabilization of the station in space, an onboard digital computer -
and autonomous space navigation system. The orientation system goes into _
~ operation on separation of the automatic station from the last stage of the E
_ booster rocket, and it functions for the entire flight time. The optical- - electronic instruments define the location of the AMS with respect to the =
sun, and by using the gas jet microengines the automatic station is oriented
in space in a position insuring normal functioning of the heat control sys-
tems, the power supply system and so on. With an increase in the distance
between the earth and the automatic station, the orientation system, simul-
_ taneously following the sun and the star Canopus, positions the automatic _
station so that the highly directional antenna will be oriented toward tne !
, earth. -
- The autonomous control system permits stabilization and control of the sta- -
tion during operation of the last stage of the booster rocket, during correc-
tion of the trajectory and braking. When making the first two corrections
= data are transmit,.ed to the onboard digital computer over the radio link to
- the ground on the magnitude and direction of the engine thrust required for -
making these maneuvers. The onboard digital computer also receives informa-
tion from the gyrostabilized platform on the position of the automatic sta-
- tion in space. Processing the information, the onboard digital computer -
issues commands for turning the automatic station and for switching the en- _
gines on and off, and the autonomous control system performs these operations.
~ 66
FOR OFFICIAL USE ONLY
w~
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFrICIAL USE ONLY
I'igure 7. Reentry vehicle of the "Mars-3" station: 1--automatic martian 'station; 2--aerodynamic brake cone; 3--radioaltimeter antenna; 4--parachute -
container; 5--antennas for communications with the orbital stations; 6--
eng:ine for wir.ding in the expended parachute; 7--engine for departure of
the reentry vehicle; 8--instruments and equipment of the automatic control -
system; 9--basic parachute ~
In order to insert the station inta the given artificial Mars satellite
- orbit and provide the required conditions for entry of the reentry vehicle r
into the atmosphere of the planet, an autonomous space navigation system is -
used. This system permits correction of the station trajectory as required
on its approach to the planet. The optoelectronic instrument determines the ~
~ actual position of the reentry vehicle with respect to Mars and transmits
the data to the onboard digital computer which calculates the operating time
_ of the engine and determines the orientation of the station space required for the trajectory correction.
The onboard radiotechnical complex together with ground units makes it pos-
sible to take trajectory measurements, receive commands from the earth,
transmir telemetry and phototelevision information, receive and record the
inf:ormation coming �rom the reentry vehicle to the orbital station for sub-
- sequent transmission to the earth. For communications of the orbital sta- -
- tion with the earth, two radio channels are used: a narrow-band and a widP-
band channel. The narrow-band channel is used for trajectory measurements =
- and transmission of telemetry data. It operates on decimeter radio waves.
The wide-band channel using centimeter waves permits transmission of large
. volumes of information from the phototelevision units and scientific in- -
struments. In the interplanetary flight segment and in the artificial Mars
67
rOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY I_
- satellite orbit, radio communications with the station are maintained through
the low-directional antenna system, and the station is oriented toward the
~ earth through a parabolic antenna. The radio complex includes the receiving,
- transmitting and program-timed devices and the telemetry, television and an-
tenna feeder systems. _
= In order to supply electric power for the onboard equipment, a solar cell
and chemical current sources are used. During the entire flight the solar
- cell charged the buffer battery of the orbital station and supplied power =
- to the equipment operating in the breaks between communications sessions.
The electric power supply for the equipment during the communication sessions =
came from the buffer battery. The independent battery of the reentry vehicle
was charged before separation of it. The heat regulating system of the orbi-
- tal station is made up of vacuum shielding heat insulation, special heat con- _
trol coatings and an active closed circulating system with the radiator heater _
constantly aimed toward the sun and the radiator cooler making contact with =
the cosmic environment. The heat exchange agent is the gas filling the IC.
_ The gas is circulated by a fan. The engine provides for trajectory correc- I
- tions of the station and braking on insertion into the artificial Mars satel- i
" lite orbit. It is made up of a liquid-fuel jet engine with a fuel-feed pump- i
ing system, control units and a fuel tank module.
I-
The "Mars-2" automatic station was launched on 19 May at 1923 hours. The
. station was first inserted into an intermediate orbit as an artificial earth = satellite. The launch from the earth orbit to Mars was made at 2059 hours.
The last stage of the booster rocket gave the automatic station a velocity ,
close to the second escape velocity. The "Mars-3" automatic station was
- launched on 28 May at 1826 hours. The system for insertion of the "Mars-3" -
automatic station into the flight trajectory to Mars was the same as the in- '
sertion system for the "Mars-2" automatic station. During the flight to _
riars, in order to insure the required accuracy of rendezvous with the desti-
nation planet, trajectory corrections were made for the stations. After the
third correction on 27 November the "Mars-2" automatic station assumed a
trajectory passing 1380 km from the surface of Mars. A capsule was separated
from it which reached the planet. On the same day at 2319 hours, a braking I
- maneuver was started. As a result, the speed of the station diminished, and
it went into artifi.cial Mars satellite orbit. On 2 December, after the third
and final correction, at 1214 hours the reentry vehicle separated from the _
"Mars-3" automatic station. The orbital station continued its flight in the
_ trajectory passing 1,500 km from the surface of the planet. The braking en- i_
gine provided for insertion of the orbital station into Mars orbit. '
The system for descent of the reentry vehicle to the surface of Mars is pre- _
sented in Figure 8. The engine of the reentry vehicle providing for conver- _
- sion of the vehicle to a trajectory for rendezvous with the planet was switched ,
on 15 minutes after separation of the reentry vehicle and the orbital station. I
- Then the reentry vehicle was turned to insure the required angle of attack ~
when moving into the atmosphere. At 1644 hours, aerodynamic braking begin,
- during which the stability of motion of the reentry vehicle was provided as
68
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
Figure 8. Landing pattern of the reentry vzhicle of the "Mars-3" station. -
Key: 1--separation of the reentry 5--starting the soft landing engine
vehicle and release of the parachute
2--starting of the reentry 6--reentry vehicle on the surface
vehicle engine of Mars in the operating posi-
y 3--aerodynamic braking tion -
_ 4--releasing the parachute provisional boundary of the atmosphere -
_ a result of the shape. Descent in the atmosphere above the martian surface
lasted a little more than 3 minutes. At the end of the braking section, on
= command from the overload sensor, still with supersonic flight speed, the
~ pilot parachute was released followed by the main parachute with reefed can- _
- opy. When the reentry vehicle braked to near sonic velocity, on signal from
the program-time unit, the p-rachute canopy was completely opened. Simul- -
~ taneously, the aerodynamic cone was released, and the radio-altimeter antennas
for the soft landing system opened up. At an altitude of 20 to 30 meters,
on command from the radio altimeters, the soft landing braking engine and
- the program-time unit giving the operating sequence for the automatic martian -
= 69
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
ue
b.
d.
c.
e.
_ Figure 9. Schematic of the interplanetary flight of the "Mars-2" "Mars-3"
- stations
; Key: a. 1, 2, 3--trajectory correction d. Earth
b. 4--separation of the reentry e. S--braking of the station -
vehicle from the orbital and insertion into Mars -
- station satellite orbit -
_ c. Mars
- station on the surface of the planet were switched on. At this time the
parachute was jetissoned to the side by a jet engine to keep the canopy from
_ covering the station. At the time of landing, a special shockabsorbing sys-
tem protected the automatic martian station from possible damage. -
= The landing site of the automatic martian station was in the southern hemi-
= sphere of Mars between the Elektris and Phaetontis regions in the area with =
_ the coordinates of lat. 45�S and long. 158�W. A penant with the USSR hammer -
and sickle was on board. The station was put into operation 1.5 minutes after
landing, and at 16 hours 50 minutes 35 seconds, the transmission of video -
signals from the surface of the planet began. They were received and recorded
onboard the "Mars-3" artificia] satellite, and then they were transmitted to
the earth in the radio communic tions sessions. The video signals received
from the surface of Mars were short-lived (about 20 seconds) and ceased
suddenly.
70 `
FOR OFFICIAL USE ONLY -
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
- By using the instruments onboard the "Mars-2" and the ".Mars-3" stations, a
very broad and varied scientific research program was carried out. During -
~ the flight on the path from the earth to Mars, the ion and electron spectro- _
meters regularly measured the energies of solar wind particles, the compo-
sition of the particles and the temperature and speed of individual com-
ponents of the solar plasma. The magnetometers performed measurements of the
- parameters of the interplanetary magnetic fields. The electron concentration
in the interplanetary medium was determined for which data was used on the -
nature of the propagation of radio waves on two coherent frequencies. On
- the "Mars-3" automatic station, in addition, a joint Soviet-French "Stereo"
~ experiment was performed to study the radio emission of the sun. Studies -
, were made of the spatial structure, the direction and mechanism of the radia-
= tion process. The same equipment was used for scientific research performed -
from the artificial Mars satellite orbit. A study was made of the nature of
the flow of the solar wind past the planet and its interaction with the iono-
sphere of Mars. The charged particle spectra and variations of the magnetic
_ field were recorded.
Scientific equipment for measuring the temperature and pressure of the atmo- -
sphere, determining the chemical composition of the atmosphere, measbring
= the wind velocity, determining chemical composition and physical-mechanical -
- properties of the surface layer and also obtaining a panoramic view using -
- television cameras were installed on the reentry vehicle of "Mars-3" auto-
_ matic station. The sudden cessation of signals from the automatic martian '
station prevented scientific information from being obtained.
In order to perform the studies of the characteristics of the atmosphere and
' the surface of the planet, the following scientific equipment was installed -
- on the "Mars-2" and "Mars-3" orbital stations: an infrared radiometer for
measuring the brightness temperature of the planet in the 8-40 micron band; -
an infrared photometer for studying the surface relief by the intensity of
the C02 absorption bands; an infrared photometer for determining the water
vapor content in the atmosphere of Mars; a scanning photometer for studying ,
the brightness distribution of the planet in the 3600-7000 A band; a radio
- telescope for measuring the radio emission of Mars on a wave of 3.4 cm per- ;
mitting determination of the intensity and polarization of radio emission
of the surface layer of the planet; the ultraviolet photometer for determin-
_ ing the density of the upper atmosphere of Mars and the atomic oxygen, hydro- '
gen and argon content in it; two phototelevision cameras with different fo- -
- cal lengths. The atmosphere of Mars was also investigated by measuring the _
- refraction of the radio waves emitted by the automatic station during its -
- passes behind the disc of the planet. -
The "Mars-2" and "Mars-3" automatic stations functioned for more than 8 months.
The "Vertikal'-II" geophysical rocket was launched on 20 August to an altitude
of 463 km under the program for joint space research by the socialist countries. -
= 71
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
-Y
FOR OFFICIAL USE ONLY
- '1'lle "Verti1cal`-II" roclcet was designed for continuation of the compleh studies -
of the ultraviolet and x-radiation of the sun, the parameters of the ionosphere
ancl meteoritic particZes, Tlie nosecone of the rocket was made up of a recover- ~
- able container and instrument compartment, The recoverable container of the
~ rocket included equipment for heliophysical research (the Polish People's -
ltepublic, ttle USSR) and instruments for studying micromeLeorites (the Hungarian
, People's Republic, the USSR, Czechoslovakia). Equipment was installed in the -
~ instrument compartment for heliophysical and ionospheric research (the German .
llemocratic Republic and the USSR). The total weight of the nosecone of the -
rocket with the scientific equipment was 1300 kg. In the area where the
"Vertikal'-II" was launched, measurements were made of the radia wave absorp-
ti.on on .frequencies of 1.0, 1.5 and 2.0 megahertz using the "AMA" ground in-
:;tallation (the German Democratic Republic). On the descending section at
- an altitude of 90 km, tlie recoverable container was separated and landed us- -
' inb a parachute system. _
~ -
''I'he ".Lntercosmos-5" artificial earth satellite was launched on 2 December.
It was designed for continuation of the studies of the radiationcondiCions in
near-earth space, the study of the dynamics of corpuscular flows in the near
outer space depending on the solar activity and to study the nature and the
spectrum of the low-frequency electromagnetic oscillations in natural plasma.
- '1'lie space experiment was performed as a continuation of the research started on the "Intercosmos-3" artificial earth satelli_te. Scientific equipment was
' installed onboard the "Intercosmos-5" satellite for investigation of the com- -
position and time variations of the charged particle fluxes (manufactured in
(:zechoslovakia), for recording and analysis of the spectrum of low-frequency -
electromagnetic waves and signals in the wave band from 70 hertz to 20 kilo- =
- Iiertz (manufactured jointly by the specialists of the USSR and Czechoslovakia),
; a special telemetry system for transmission of inrormation in a wide frequency _
- spectrum to ground receivers (made in Czechoslovakia). Simultaneously with
the operation of the scientific equipment on the satellite, the ground geo- _
physics stations and observatories of a number of countries measured the
low-frequency radiation of the upper atmosphere and ionosphere of the earth _
under a coor.dinated program.
_ The "Oreol" art.ificial earth satellite was launched on 27 December. The pur-
= pose of this experiment was to study the physical phenomena in the upper atmo-
sphere of the earth in high latitudesand to study the nature of the aurora =
= polaris. The scientific equipment and the experimental prooram were developed
jointly by the Soviet and French specialists within the framework of the
Soviet-French "Arkad" plan. The scientific equipment installed onboard the
"Ureol" was designed for studying the proton and electron spectrum in a wide
- range of energies, measurements of the integral intensity of the protons and
determination of the ion composition of the atmosphere. In addition to the
= scientific instruments, the following syGtems were placed onboard the satel- _
= lite: the system for determining :he orientation of the satellite in space
using the sun sensor and a three-c.,mponent magnetometer, a radio telemetry -
- system for transmitting thP measurement results to the stations for
_ data reception and processing, the system for radio monitoring of the orbital -
parameters and the command radio link for controlling the satellite from the
ground. -
- 72
FOR CFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
a~
r-I
QN

- �r1
b
N
, U
G
. cd
r-I
11
w
cd
~
' U
- U
Cd
a
N
- �rl
~
O
U)
~4
v ~
4 1
o N
cn o
-ri
.c~ o
ro a~
4.J 4,
w bD
o (1)
v
x
rn
rn
~
u
m
.
ao
I I I
I I I I ! I I I I 1
I I I I I I I I I rn
c
d 41
ai p
O~ rn rn
�rl p
O
U 41

0
r-i r-1 r-i
R4
~rl ~
N
�
~

~
N
O
w
00 3
'a
~
M~t~~tN u'1~'~'I, 01 V1~D1, 0 chNN l!'1 rl~t~Y'
O G'+
J
. . . . . . . . . . Lr) . . . . . . . . . .
�rI �rl �ri
1,
M I/1 1, Ol cV %O l1 01 -,T 00 O) O 01 01 01 M 00 M I~ 00 M r-~ N O) m
lr1
00 rn rn 00 m m m 00 ~-1 00 00 H a0 a0 00 O m 00 m 00 00 O O O a0
r-i
41 ~
r~l r--I rl r-i r-1
r-i
o a
~ ro
o
cb ~ G
o 0 0 o M o 0 0 0 0 0 0 0 0
0
1.J �ri O
N ON -.t 00 10 00 Q% It O\ cY1 M NID ~O
u1
�rl rl �rl
NIp
o o . o - � o . o o . o
�
0
0
0
.a U 1.~
u'1 r-I r-I ~1 ri u'1 't U1 u1 ri ul Ul N
~fl r-i V1 rl rl rl r-I rl -It
u'1
N
-It
34 0
%D 1, 00 %D f, ~.O 1~ %O ~'D L/'1 %D %D I~ %1O 00 "O 00 00 00 Lf1 V1 t- 00 t, %.O
t,
O H
N
N
b0 ~
00 t, O I- MIt NY' N M%D 01 V1 %O '-I lZ ri %D M O O 00 O% r-I U1 I-
00
�H
u"1
Ot, MOoOt- chr-I01m Ornr-I%Or-Iri t- N04 0 0m r-1o00
O
~
N N%ONN u'1u'1N ~1r-iN01NNN00 %ON%ONN nNr-IN
-t
v
r-i
r-i
Q+
Q1
N~
%0 O0M ON OA OOI- ',OO%ONM r-iM %O-t %pN%O-,t NNO
O
bD
M N r~ O r-1 rl 1~ e-I r--I I~ r-i r-I N I- tf1 Q O %O .7' N~,t d' -t N O
M
O
N00 %OMLf1%0 V) MMNMOMNNOI- N%.ON NOOu'1NC*1
u1
N r-i rl r-I r-i
r-i
O r-i N M-It U1 %O I- 00 Ol O r-1 N C") I7' Lf1 I'O I- 00 rn O rl
44
O% OI m 01QN 01Q1Q% 01m 00000 00 OOOrq r-4
4-1 cd
cY'1 cf1 MM Mcr'1c"1Mm M~t.7'-It-It Itlzr O-It ~lt -td'lzt
O F+
I I I I I I 1 I I I I I I 1 I I I r-I I I I I I
00
U
cY1
M m 3-+ M tn tn M m u1 u1 m a~ u~ U] ~n tn y U~ ~+J I M u1 M m M
r-I
N 41
~ v
O O O O O O O O O O O O O O O O O O O~ N O O O O O
H ~ N ' G � 0 q q
'
~Y
�1 ct1
a1 ;P~l 0 Fa r:3 rii 5 5
~ ~
m m+J m m M M m m M m m m 0 cn m M M tJ '-I D, m m cn 0 m
z
n
w
UU~UUUUUUVUUUUU
~
U UU
cii~nUxUUU
N~
T>1 T>1~
,z r-i r-i r-1 r-i r-I r1 r-i r-i
r-I r1 r-I
U 4J
:3 :J ~ J F+ P 1-i 3a S-I U U U �rl �rl �rl �rl �rl �ri �rl �rl �r-I �rl �rl
11
N
0 G' G' .o .n .o .n .a p 3-~ Sa 3a f-~ N~+ ~I 3-I f-~ 3a
av
tititi �tiwr~www~~~~~~a'd~~�'�~d~d~~
N-,t OrI,D m 00 00 u'1%0 M0 nr-IN-t f- ~tI- m MM~700%0
r-I rl N N N r-{ r-I N N r-I N r-{ r-i r-{ N N N N
~
CY)
O
rl
r-i N c'rl -It u'1 %O I~ 00 m O r-i N MIt L/1 1%0 t~ CO ON O r-i N M-zt Ul c"
'1
r-1 r-i r-1 i-I rl r-1 rl rl r-I r-4 N N N N N N ~
H
~
N
I3
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
,
'C7
~
~

U
G
O
U
v
~
n
rn
r-I
G

'b
~
U
~
~
ro
~
~
w
ro
~4
u
N
U
cU
a
cn
t1
N
~
O
(n
� u
G
w o
�H r-i
�H
IJ
.u
~
~
w
v~
~
i
~o a
c
da)
a) u
4.4 0
m M p
q
tJ ct1
�rl }.i
al cd
rn :j
`f)

�
p

a
i
~
~ a
v
cn cn
cd ~
v ~
4-+ ~
~
o -w
N r-i
4-1
H
~
~
G ,-i
~ ~
~
Ln Ln
� r-1
�rl r-i
P b.f.
R1
O-, ON
y cd
N
w U O
a O
O~ O~
00
I I I O�rl
I I I'b +j
.n
I I �H
I ^ I I I I ^ I 1 I
2 U
~(d
~ N 60
r-i 11
O% 01
�rl
.IJ t0
Ql rl 'r,
ci3 U
rl rl
r, 4-I 1J

U U�rl
1.J Q1
N�rl �H
N U)
N�rq 'b
�rl S-i
41 p
cn p
A.C q
.n
O R1 O
H
N'J r-i
O U
O
cd
-1-
I, Uo
rlNIt'CJ
N MM
I- rl MO%D 00 O
. .
U)
. . .
. . .
.
.
. . . . M . . I
f~
I~ 00 N!-+
u1 N O~ N
~1 01 00
O~ O~ I~ O
~ O~ Q~ ~ O~
00 00 rn.~
O rn 00 r-i
ON O 00
00 c0 rn CO 00 ..C 00 a0 00
r-1
r-i
00
r-1
r{
r~
O
O R
O
O
O O O O O O O O O O
~T CA Ul
, t
~
11 00 N 00 7' ~t 00 00 ~1 1O
~p
�o
0 0 �o
0 0
r-i r-1 ,--I 00
-7 r-i Lr1 O
d' -t r-i
N i-I ri ~--I u'1 u1 r-i r-i M rl
U'1 t!1 I- IT
t- I- %~O %O
1- I- u'1
I- iI1 00 u'1 'O ~.O tf'1 ul ~J' u'1
Lr)
U'1
CO O M O
I7 N-It 00
r-{ Lf1
r1 00 CO -It %1O O N m Ol I-
ir'1 O c0 00
ON 00 rl N
~ m 00
~-I O r-i O O I, O O vl O
r-{ ClI N M
O% N N vl
Ul M rl
N N ~O N N-11 N N rl r-i
-4
r-i
O
lzr N N O
O r-I M p
~ N I-
I- rl O O N O N N M t/'1
.7
t- It M O
N r-i O u)
Lr1 r-1 r--I
M t- u1 %.O N O%.D ~.O V'1 CO
r-i N-Z? O
O u1 M~
ul O N
C''1 N%O N m M N N N M
u'1
N
01
C\i
N
ch
al O r-I
N M~7
U1 "O
t~ CO al O rl N N~t
r-I N N
N N N
N N
N N N m rl M C'1 M M
.t r-1
d' ~Y' -t -t I d' ~t .t
i I I
I 1 I
I I r-i
I I I I cd I I I I
fA U) (A M
3 tA (A M
(A (A 1
m (A p fA (A (A [A fA fA
M
O O O I
O O O I
O O N
O O O O O�rl O O O O
N
l5rn:j
(!l U) Ul S-I
In (n fn S-~
(!I (n >1
U1 fn 1J m fn r-I (n m fn fn
w
w
�
�
�
�
�
�
�
�

xc
)c
~
n
c
~~c
c
~~�~c
~~~~�c
~~c
~
41 +1 4-1
n1 N
N N>I D,
71 D, D,
'J,
r-i r-i rl bD OD bA
cd cd cd cd
cd cd N 4S
c`l
z z z x
z z z z
z h ti
h7
Oo0m O,%
N I- 00o0
01It "0
r-I-It ~-00MCA0L/'101N
r-i r-I rl r-i
N N N N
N
rl N rq N N N Cn rl
-It L/1 %o I-
00 O\ O rl
N M-It
L/1 ~10 1- 00 01 O r-i N C"1 ~T
r-I
MMCY'1M
Mm -tIt
~'d'It
~t~t -It -7-IT UlUlL/'1L/1 vl
74
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
m
~
'l7
41
~

L
G
O
U
~
r-I
~
~
r-I
G

b
a~
~
u
a
~
co
-4
+1
w
ro
u
UJ
u
co
a
U)
41
a)

~
0
cn
U
~
C'.+
�rl
rl
O
~
~
G7
N
~
~
E?
O
t
A
N
4a
-ri
O
rl N
1.J ,0
~
0
U ~
4..I
vl
Cl
-W
I
4-4
I I I0) I I
O
I 1
I I I 1 I 1
I 1 I I
00
a)
~

U
~ -W
m -rl M
�rl �rl
O
~
r-i
~
N
'U G
.ri T1
~ C/~
N O
.r.{ +1
4J
U
rl
N-rl
p Q)
W
~
Cd
~

03
0
O
H O
00 �rl
.o
m
~
r-I
N M u'1 't M N p -ri
a) tn %O
rI N N N I- u'1 ,.L:
rz cn ~7 N
a~j
En
I~
N
I
Ln u1 a1 Q1 l/'1 O~
01 M r-i
Ol N 01 N 01 O~ ~-1
~O N 01 t!'1
m
al (M 00 00 m 00 N r-I
u'1 00 00 r-i
00 rn 00 m00 O r-I
It 41 00 C7%
0
0 o v')
o 0
0 0 0
0
M
O~ d'
~1' O~
00
0
0 0 � o o
. o
0 0 � o � o
o � o
r-I
I
~t -It u1 ul r-i LIl O
. N ul ~t
Ul rl u1 ~1 NIt Ln
r-I Ln -~t
I~
I- %O ~ I- %O ~t
i, %.O I~
%D I~ kD t, fl- 1- %O
%O I,
N
-T M N M N 41 O
r-i r-I Ul
r-I ri O N00 N O
r-i %O O
DO
I
r-I Nr--I r-I CO O d'
r{ r1 r-1
O 00 r-i 00 rl 01 %O
00 N N
N
L11 V1 N N N N r-I
' N N-T
N N N N Nr-1 :T
N N Lf1
r--I
r-{
Ln
O 00 r-i 00 IT 00 Q
r-i Ul O
O N-It I'O 00 QN O
c") I, M
-T
O
~
t!'1 t!1 N O r--I 00 ~t
N N u1
I- N 00 rl N c`J Lf1
c4 I- M
u1
u'1u'1MMOONrI
Mc'1u'1
NLn N u1MN M
u1N Lfl
-
M
u1
%~O I- CO O% O rl
N Mt
N M~T L1'1 %.O f,
00 m O
c''1
c7MMM"7'"t
-It It -It
u'1L/lu'lu'1U1LI1N
ulu'1"0
~t
~t -t
-zr -t -t .t I
.t ~T -11
~
ao
1 1
1 1 1 1 ro
I I I
m
Ln
~i
m m m (n cn ri) ~
Cn m (n
U) (a (n m cn a) p,
rn cn 0)
o
I
o 0 0 0 0 o I
o 0 0
0 0 0 0 0 0�~+
o 0 0
r ~ ~ ~ cl
~ ~ r
r4 r 5 ~ = r
z ~ o
Ln
G
m U) cn Ln cn m0
cn m (n
'
m m m m m m 1-I
cn cn cn
o
:j
o O O o O o:j
` o O o
o O O O o 0 o
O o 0
a~
0 w w w w v w
a)
p p
N~+
.o a .a p
a
F+ 3~ ~ N ~ a1 al
~ N ~
~ ~ ~ ~
P 4l N
.a .a .o
cn
N
~ U1 41 N aJ N N
N.~1 .O
.r~ .a ~ z
F~
:j
41
41 4-+ ,j 41 +1 41 4-1
41 o 0
0 o a) w w w w
en
a
aaaaaaa
a+1 +1
.u+1 > > y p>
p> >
N
:1
N
41 N 4J N Nw N
(D U U
U U O O O O O
O O O
Ux
tA : cn O_ -
rl c0 ri Nr.
a O
0 3
3
tn H Z- (n U) cn tn = =
NU) H= cn = cn
tA
.
.
iua a I
r-I Nm zr vl ~D 00 m O
e-1 N M~7 L!1 ~D f-
o0 m O rl N m ~7
vl ~D
r-{
r--{ r-{ r--I r-i r-1 -I
r--1 r-1 N N N N N
Q
N N
103
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
I FOR OFFICIAL USE ONLY
~
-
'l7
41
~
G
~
~
O
U
_
.--I
n
rn
~
b
_
y
_
.C
U
~
~
cd
-
.-i
a~
_
44
ct
~4
41
-
U
c0
-
P.
-
ao
41
-
C1
>
O
~
I
~
~
O
_
z
r-i 1-1
~
0 c0 'O
c
O
O
O M N CO O N O nm u'1 N m Lr'1 v1 c'1
rl O C+'
m
O
0 r-I%0 ~T%0 m .7r-I%0,.DOLn N 0 aOc"1M r-i
I 1~ rl ~rl ~r-1
rl .O F+ ~
I
rl
N
N f:~ O CO ~7' N C'1 17 14 O O1D u'1 a0 ~D V1
~ H C!
O
O
OoN 0a00% r-ION O1% 00rn0 CY'1M%Orn0 c*1
H O P.
r1
ri
rl r-i r-i r-1 r-i r-i .7 .1 .7 r-1 .7
r-1 r-I r-I
0
o
O O o O o 0 o O O o 0 0 0 0 0 o O
I ~
~'1
N
N O%O u1 I~ %O c'l ON kO N~7' ~D O 00 00 m o O
-r-I O
%D
%D
%OOrIrnOOr-i O m r- m Ot-~cq u1rnOM
r-i
r-1 rl
.
.
. . . . . . . . . . . . . . . . . .
ctl
fJ J-i
t~
I~
n r-1 O~T u'1 N M M 00 N O N N N M N O O
rl
CO
00
AO
CO rl U'1 1, f- Cn M fn m Q% r-1 00 00 f-~

-I
H C.'
ti
9:
ti
-I
kD
-1
-1 cv1 -;t u1 t- u1 -i r-I t- r1 L1 rV 1- r- 00 -.,t rn O
Gl
r�1
r-i
rIN0--T 0%.0 f- nnOr--IdO~D%DOm Q% (7N
W
GJ ~
O~
m
ON -.7 O% N u'1 f- u'1 u'1 00 00 ~7 U'1 -~T %zr ON u'1 a% t,
O
00
rl r-I %D "O iO U1
4.3
O
' c'1 cn N m
!
4
H
t~ O
~
0!
Ol
O~
O
O 11% c0 %O N rn r1 a0 t- N~7 t-~ r- ri c�1 %D v1 U1
~
G!
m c'') I, u1 ON %D N CT m 1l- M-T %D -.T M I- CO r-
00
1-
t~ .--i %G r1 -4 GO M cr1 I, rl~ r-i u'1
O ~ N.7 O% ~
1a
rl
`
c0
H
ch cn c'7
a
a~
a
r
a~
1-i
M
o0
~r-I GO
rl 114
-O
H
,
.7 1-,T 1 I vl +1 O %.O O O N O r-
rl
cn 00 %D r1 N 1 1 I%D O 0 L/1 'O I o0
y .
w L/'1 u'1 r-I cr1
il
�
r-i
ci 41
w
O
U
00
40 W ON 01 ON O O O O r-1 r-i N N N
~ C.
O
O O O O O r-1 r-I r-i r-i r-i .-1 r-i r-i r-i
~ ~
. . . . . . . . . . . . . .
R1 td
~
N%.O O 00 01 -.7 n M o0 M u'1 r-i .T O
Q r-i
r-i rl rl N N r--I r-A N N r--I 1-4 r-i N
A
A
A
O G
- N
'
0
~
O
~
~
H t~
H
U ~
-i 3~+ G t~
W G +
41) a)
-
00 GO
H N r-i 4! (L) H$4 H 41 G
tJ .~G
44
G O
H 00 a) A GO Hp H 40 a)
(A U
C rl 3-+
H Q A Q', H G', H C, CJ
00
v)
uva
- i- i a~ i
o t+
ca
r: w
in v w v o x r~ 4.3 +J b m
aa
r-i
:3 oa
ta :3 cc -T m i cd co u m :.I a cc Cd
1J
cC u F
+-1 O H � I w w p " m O O f+ r-i
ri U tA
rl U O ~ O O 0 -r1 r-i -r1 U U O 11
-
~N
Htl) H ~F HHHPci Hcn cn E-+d
~
~
~
Z
w
ai
,ri 3
3
co
cd
+-1 o
0
o cn
v
H
cd ~4
r-4
U3
~
w
w~vr-I
r-I
a cn
cd
G
O ~ O
O
"
q
,a
a ..C
c

t~+
~
cd b0~
i.
rl H
~
r-A
P
~
d
c
Ei
q
.0 7, ~C
-zr
~
G
o 3 G
~
~
g
~
v
f

H
Ll
4-I W
:1
1.1
rl N H H ~ G1 r-I H 1-+ C4
R1
:j
O 0 ~
0

UI - u 1-~ :4 H H u yC u 0. H H O~A 1.i cn
Cn
O
O O
O
C1 ~ 41 ~ G>
H w 41 ~ v) I I r-I 41 a1 P-4

~A r:3 =
~
.r-
,
1 1 4-J P o cn cn a -.A W w
r-i r-i u
:j
u
oour+ u u.[ocn u m up U u ?C p uE-4
-i
cd ,H ,H
r-1
,A
cd 0) r, (1) Q) cn cn E-+ 431 -4 (L) a cn cn z
3
.0 w 3
cc
3
E En tj:! cn tn = o E- cn = cn =~1 A- ~ cn r-a
-ori maiI
'
'
~
,
N
N
N
)c`
MMMCr1MC`
1M m --T -11
-IT --T --7-:T -It
104
FOR OFFICIAI, USE ONLY
r--~
DO
td
a
bo
~
3
0
~
r-I
O
W
~
O
tA
N
a~
O
G
N
~
~
u
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL U5E ONLY
[Notes to table on preceding pages]
1) The parameters of the final orbit close to stationary are indicated.
_ 2) According to unofficial reports, this is a satellite for radiotechnical
reconnaissance.
3) According to uiiofficial reports this is an IMEWS satellite (according to
= other data, two IMEWS satellites) weighing 0.7-0.9 tons for early detec-
tion of rocket launches, recording of nuclear blasts and the performance
- of o"her missions of a military nature. The values and the parentheses
- indicate parameters of the transfer orbits in which the target was left.
It was not successfully inserted in the calculated orbit close to station-
' ary. (For information on the preceding launch of the IMEWS satellite see
_ YEZHEGODNIK BSE, 1971, page 509, Table No 33).
4) According to unofficial reports, this is the first LASP (Low Altitude
Surveillance Platform) photographic reconnaissance satellite weighing
- approxim.ately 10 tons. �
,
- FOOTNOTES
" 1. Interplanetary Monitoring Platform--platform for studying interplanetary
_ space.
2. Solar Radiation.
3. Small Scientif ic Spacecraft.
- 4. De�ense Satellite Communication System.
~ 5. Space Technology Program.
6. Astex (Advanced Satellite Technology Experiment).
7. Scientific Instrument Module.
BIBLIOGRAPHY
AEROSPACE DAILY, AIR ET COSMOS, AVIATION WEEK AND SPACE TECHNOLOGY, FLIGHT,
INTERAVIA AIR LETTER, NASA NEWS RELEASE, SCIENCE NEWS, SKY AND TELESCOPE,
SPACEFLIGHT, SPACE WORLD.
COPYRIGHT: IZDATEL'STVO "SOVETSKAYA ENTSIKLOPEDIYA", 1972.
105
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
SOVIET SPACE RESEARCH IN 1972
- Moscow YEZHEGODNIK BQL'SHOY SOVETSKOY ENTSIKLOPEDII in Russian No 17,
1973 pp 522-529
- [ArLicle by L. Lebedev]
[Text] In 1972 automatic stations were launched to study the moon and
Venus. Launchinss of artificial earth satellites for scientific and
app_lied purposes continued, and a comprehensive program for studying the
planet Mars with the "Mars-2" and "Mars-3" automatic stations (which were
put into circumplanetary orUits in 1971) was completed:
On 14-25 February the earth-moon-earth flight of the "Luna-20" automatic
station (AS) took place. Samples of lunar soil were transported to earth;
they had been taken from the remotP bedrock region of the moon for the
first time.
Structurally the "Luna-20" AS (Fig 1) is the same as the "Luna-16" AS (see
YEZHEGODNIK BSE 1971, pp 493-494) and consists of a landing stage (LS) with
a soil-intake device (SID), on which the "Luna-Zemlya" rocket with a
- recoverable apparatus (RA) is installed. The "Luna-20" flight configura-
= tion was similar to that of "Luna-16." A multistage rocket with the
- "Luna-20" automatic station was launched on 14 February at 0620 hours.
The station was launched towards the moon from an intermediate orbit as
an artificial earth satellite. 3o that the AS would reach circumlunar
space in the assigned region, the flight trajectory was corrected on
_ 15 February. On 18 February, as a result of deceleration, the station
was inserted into a circular selenocentric orbit with altitude 100 km,
inclination 65�, and orbital period i hour 58 minutes. On 19 February
_ the station was transferred to an elliptical orbit with aposelene 100 km
and periselene 21 km.
To land the "Luna-20" automatic ;tation in the calculated region of the
- moon on 21 I'ebruary, the main retrorocket engine was engaged at 2213 hours.
106
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
F0R OFFICIAL USE ONLY
[+Iithin 267 s the engine was disengaged, and the station executed a free
Eall to an altitude of 760 m. From then on, the station descended in a
controlled descent mode, during which the thrust ot the main engine was
- altered with the automatic control system. From an altitude of 20 m
from the lunar surface, the low-thrust engines effected deceleration.
At 2219 hours on 21 February "Luna-20" soft landed on the lunar surface
at a point with selenographic coordinates lat. 3�32' N and long. 56�33' E.
- The station's landing site was located on a region of lunar bedrock that
adjoins the northeast end of the Sea of Fertility. After the station had
- landed, the on-board systzms were checked, and the position of the station
- on the lunar surface was determined. A telephotometric device took images
_ of the lunar surface which were then used in the selection of the site for
= taking samples of lunar rock. Then, at the command from earth, operations
to collect soil were started. The SID drilled the lunar ground and
col3er~ted roclc samples. Due to the increased resistance of the surface,
drilling was done in several stages, with intermittent stops of the drill-
ing device. The samples that were taken with the operator were placed in
a container on the rocket and hermetically sealed.
The "Luna-Zemlya" rocket was launched at the command of the onboard
' program-time device on 23 February at 0158 hours. On 25 February on the
final segment of the flight back to earth, the RA was separated from the
- rocket. After aerodyna-inic deceleration had occurred ir: the dense layers
of the earth's atmosphere, the parachute system was put into operation and
~ at 2212 hours the "Luna-20" RA (Figure 2) soft landed in the calculated
area 40 km northwest of Dzhezkazgan. The lunar soil delivered to earth
_ was taken to the USSR Academy of Sciences for analysis.
, On the whole the soil or regolith collected by "Luna-20" (Figure 3) is a
- loose material of different grain size, light gray in color, considerably
lighter than the regolity from the Sea of Fertility. As compared to the soil collected by "Luna-16" it consists of noticeably fewer fused par-
= ticles. As in the case of the soil from the Sea of Fertility, that from
_ the bedrock region of the moon has a high capability for electrification.
- The bulk weight of the soil is 1.1-1.2 g/cm3. It is easily compressed to
1.7-1.8 g/cm3. According to the data of granulometric analysis, the mean
A particle size is - 70-80 um. There are more large particles over 1 mm in
size in it than in the soil collected by "Luna-16." The lighter shade of
the "Luna-20" regolith is confirrned by a study of the albedo. The value
= of the albedo is higher than in the samples bret;ght by "Luna-16," "Apollo
11," and "ApoJ1.o 12." For the fines the albedo equals 0.083, for the ultra-
= violet region--0.145, for the visible region--0.200, and for the near infra-
' red--0.260. The maximum reflection occurs at a=4 um and equals 0.370.
A microscopic study of the regolith from "Luna-20" revealed a sharp dif-
~ ference between it and the marine regolith from "Luna-16," "Apollo 11,"
- and "Apollo 12." In the regolith there is a dominance of fragments of
crystalline rocks and minerals with well preserved edges and chip surfaces.
107
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
r-i
i~
I'igure 1. "Luna-20" Automatic Station
Key :
1
Instrument compartment of
7.
Drilling mechanism
.
landing stage
8.
Drill rod of drilling mechanism
2.
Controlling jets
9.
Telephotometer
3.
Rocket propellant tanks
10.
Propellant tank
4.
Antenna
11.
Engine unit of landing stage
5.
Instrument compartment of rocket
a.
"Luna-Zemlya" Rocket
6.
Recoverable apparatus
b.
Landing stage
~
Figure 2. Recoverable Apparatus of "Luna-20," Station
108
FOR OFFICIA:, USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
~
Fif;ure 3. Overall View of Lunar Soil Delivered by the "Luna-20" Station
Few scorified breccia and spheroids, which are characteristic for the
regolith of lunar seas, are observed. The main mass of the particles is
composed of rocks of the anorthosite type, consisting to a considerable
measure oE feldspar (plagioclase). In them inclusions of inetallic iron
of varying shape and are constantly size encountered. Rocks of the basalt
type are represented by a few particles of basalt that are completely
anal.ogous to the basalts of the lunar seas. In the fines of regolith
(,.c
~ N~

o 0 o i
o 0 0 0 0 0 0 o
p o 0 0�H U
~ G
o 0 0
0 V~i
(1) v
cn
cd
'
~ F3 F3 q~~ F~ F~
Ul U] !n (n
n
aI v0~3
f: t1 (n ri N
U] F+ (n
U
(n (n Ul ~
+
O O O~

U] (!l !
O O O O O O O O
N a1 O O O p
O0) O
z
0 ~U a
0 ~u u u ~~u
> u u~w

a
H
U)
�C
G G
H N
F=
'
F=
P+ 44
+
+
ci3 "C7
N
N tl1 M~t
,o U'1 -1 ~t vl N t!'1 Ul
I- O r-i Cy'1
'
1 M
r..{ N r{ N N N N C
a)
r-
i rl N c*1 d'
vl ~,O t, 00 O% O-i
00
z
r-1
r-I r-I r-1 r-i r-I
r-i N N
4.3
H
122
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
14
a)
~
'b
41
~
C"+
.r{
~
~
O
U
v
N
n
O~
r-I
~
.r{
b
~
~
U
:j
cd
r-1
JJ
44
~
~
U
N
U
cd
a
~
J-1
N

7
O
cn
~
~
0 0
,1 o
~
~ v
~x
a~
0
~
3
~
l
oo
rn
~ o
rn o o
rn
rn 0
%
C
4
u ~
.c �H
00 .n
�ri P
W o
~
Ln
.a r-i Crl u'1 d' -It vl 00 00 M%.O .C %O %0 N r-I N N 00 N d' N
c+'1 00 -:r
.
I, O~ N O~ O Q~ r O~ O~ O O~ O; I, N NL/1 M N O~ u'1 00 O~ Q~ L/'1
E
Lr'
~ Q~
t~
m 00 m 00 r-i 00 r-i a0 a0 O a0 a0 m m m rn O ON a0 m O o0 00 r-i
00 00 O
0 0 0 0 0 0 0 0 0 0 0 0
0
'7 ~7 "O N 00 u'1 '1' ~1'
't
o . o � o � o 0 0 0 � o � o � o . o � o
� o 0
IC
u'1 r-I rl tf'1 -t u'1 ul tf1 Ul u'1 ~t LI1 rl ul 00 rl r--I r-i r-i ~t 00 u1 u1 ~
L1'1 u'1 M
%.O 00 I- %.D I, %.O %1D %.O %10 %O t~ %O u'1 %D It 1, 00 I, Ul fl~ ~t
00
O-It OOr10N OOm C+Ir'IWf101~N I~Nm 0IN%.OOOU'1
^m m
tr)
Lrl r-i n r-i a0 r-1 %D ri O r-I M OCN Lr'1 ~.D 00 m 00 O O N O O N
00 ul
M N N N M Nt N N N I, N rl U1 N N 00 N N tf1 N N N~Y'
N N M
r-1
01- r-Im OOOMrI00Q1QONO00N 01rIMItQN -It ~7'O
m
O%Om r-1 rlr-4 OO~tONm ~70%0 r1 Nrio0tr1~tC00-It
0N -It (Z
~t
0 NU'1cr10M m MMMOONMOu100 M uIN u1r-INC1U)
NcY) Q1%
O r-i m O N r-i
O c*1 N
N
"O 1, 00 O% O rl N CY'f ~7 ul .O QO M O~-I N M~7
N M-It
00 00 00 a0 m N O% m m O% Oh O% N tA rn m GN O O O O O
r-I rl r1
0~7 ~~U'1u'1U1u'1
l
~t N
-It '7~7~t-It I -t-It ~t-t
L1'1
1
1
~
~
N
I
I
'
O N(J] UI VI fA ',a~ (!I (A VI fA N!A O fA tA S-1 (A N UI !A N fA (A
fA U1 (!1
0
~ 9 ~ ~ ~ ~ ~ 0H
0 ~ ~
-G ~ ~ ~ A ~ ~ ~ U
~ ~ ~
cY)
o
o i
0
-i
m ~n m u)
41 m
3
~
vl m (n
r
r cn
0
o m m ~n m En r, m m m m m m o
3-i O O O O O O O O O O O O S-+ N O a) O O O O O O O rl
O O O
ar.) U U 0 0~c~U CJ U vU a 4-j U Z 0 U 0 U U 0 U tn
0 U U
H
a a a ro ~ a n d ~ ~ 0 ~ ~ ~ ~ ~ ~
:j :j
~
f"] f7 p"') . h h h. . h. h~1 ~ ti ti
p") Q
i di
N
-,t ~t ,--I vn %p t- M Lrl rn r-i tn r1 %O M O 0 0 O %D O N cf1 rn O
GO N %O
r-i r-1 N r-i '-1 N N N N N N c*1 M m m r-I r-I r-I r-I N
N e-i
r-I
N cr1 ~7 ul %0 I- 00 QN O rl N M ~t u'1 %.D I, 00 M O r-I N CYl -It Ul
1.0 I- 00
N NNN N NN N M Mc"1 >
WWWWWu
u u u u u u u u u Ou�~ o 0 0 0 0 0 0 0 0 0
cncncncncno
oocooooooooozzzzzzzzzz
N
~10 00 .TrIt- M
M~DO r1%0w 010t~M OrINO -,t 0 r-It~D0000 O
rl N N
r-i r-~ r-i r-i r-I N N N c/1 cn rl rl N N N N N M cn
r-{
Ol O r-I N MIt
v'1 %O 1- GO m O rl N M-T u'1 %O I~ 00 m O r-1 N MIt ul \O ~
d' u'1 vl Ul u'1 vl
Ln Ln V1 U1 u'1 %O %D ~D %D %lO %.O %D %O %O 1.0 n I, I- I, I, n n
175
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
4J
l 1 1 .J
^
~
~
G

J-1
L~+
O
U
~
cYl
n
~ ON
~--I
.r{
. ~
a
.C
u
- ~
~
r-I
41
_ 44
cd

U
~
U
cU
a
U)
_ N

7
O
cn
�1'~ 1~ .r
M 41
0
O
~
~
~
41
" 4
0
4"4
44 4J
J
-rl
4J
co
'I'i p
Qi
w
U
t1]
N
Q)
~

UI
ia
F3
q U
4:
a~
ao
cd
o
�r
i
�ri
~
4
-
~
cd
q �
~
Q)
O
P.
o
p
o
�rj
a)
.n
-4
`d
~
d
c
u
a)
41
a1 41
m
q
�rq
4
a)
o
.a
s~ on
41

o �rA
�ri
D,
o
uw
r-i
.o
N
~
I- I, 01 N
00
00 I- N I,
I~
. r~
O ~Il Ol O,
~Y'
01 w Q~ 01 I1'1
O m CO 00
rl
00 ,C O 00 O
~-1
r-1
N r~ r-I
~
0 0
0 0
O~ "O
DO 00
0 0
0
� o 0 0
~O
~7 r-I 04 '-1

N N~t Lf1 c*1
t, u'1
t-
r- %1O 1~ I'O 00
O O-It u'1
-It
-IT 1.0 i, r- r-i
Lr1
r, 00 ,-1 N
O
r-i ~O O u'1 ON
I~NN N
~Y'
N~t~tNQ1
r-I
O rnLf'1 N
r-i
~10 u1 u1 O N
crl U1 u1 t~
r-i
It %O O% 00 c"1

0000M N
Lf)
~NO
M
~
r-i
~
~
N
~O
I
r-i r-i r-i
r-i
N N N N
~O ~D k.O
~O
%O %O
~ I
~
~ N
n1
u1 tn M I
v]
u1 u] (J)
O O
O N
O
O�ri rl O O
g
g
~
~
0
N
~
F!J �
i U
i
c r-
1
t
(1)
UUUcA
U
U~ODU
N 41
N
4J N~ Gl ~
A A A A
A
A A A A A
N
-It M I- 00
O1,
r-i u'1 %O 1- Q%
r-i r-i r-4
r-i
N N N N N
r-I
t, 00 O\ O
r-i
N MI7 u'1 ~O
n n r- 00
00
00 00 OC) 00 00
-176.
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
Artificial Earth Satellites for Applied Purposes
"Molniya." Four "riolniya-1" and four "Molniya-2" satellites were launched
in 1973 in order to maintain long-distance telephone and telegraph radio
communications, Eor the transmission of programs from the USSR Central
Television to stations of the "Orbita" network and for international
cooperation.
"Meteor." Two "rleteor" artificial earth satellites were launched in 1973.
'rhe basic mission of the satellites was to obtain meteorological information
required for use in the operational weather service. The meteorological
equipment of the satell.ites provided for obtaining images of clouds and
snow cover on the light and dark sides of the earth as well as data on the
thermal energy reflected and emitted by the earth into the atmosphere.
Geophysical studies by rocket sounding of the atmosphere continued in 1973.
COPYRIGHT: IZDATEL`STVO "SOVETSKAYA ENTSIKLOPEDT.YA", 1974
.10845
CSO: 1870
177
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
~ FOR OFFICIAL USE ONLY ~i
;
_
_ ;

~
idON-SOVIET SPACE RESEARCH IN 1973
Ptoscow YEZHEGODNIK BOL'SHOY SOVETSKOY ENTSIKLOPEDII in Russian No 18,
1974 pp 526-537
[Article by D. Gol'dovskiy]
[Text] Artif icial Earth Satellites
In 1973 18 foreign artificial earth satellites were inserted into orbit
incl.uding 16 American satellites (three in the "Explorer" series, one NOAA,
one "Transit," two DSCS, one Air Force meteorological satallite and eight
secreL satellites for military purposes), one Canadian satellite ("Anik-2")
and one satellite of the INTELSAT international consortium (the INTELSAT-
4E). The "Anik-2" and INTELSAT-4E satellites were inserted into orbits by
American booster rockets.
The basic information on the orbits of the enumerated satellites is found
in the Table. A description of some of them is presented below.
"Explorer-49" (Table, No S). The second American research satellite of
tlle RAE1 rype (RAE-B, see Figure 1), designed for radio astronomical
re5earch: recording low-frequency (0.002-13 megahertz) radio wavelength
emi5sion oE the Sun, Jupiter, the Milky Way and other galaxies. In contrast
to tfle first satellite of this type (RAE-A, "Explorer-38," see YEZHEGODNIK
B5E:, 1969, p 500), the "Explorer-49" was inserted not into a geocentric
orbit, but into a selenocentric orbit in order to avoid interference caused
by radio noise of earth origin: when the satellite sets behind the moon,
it is shielded from earth radiation. The satellite weighs 334 kg. In
structural design and equi_pment, the RAE-B satellite is similar to the
fzj~g-A satellite and, like it, it is equipped with two V-type antennas made
up of four rods 230 meters long, each of which unfold after the satellite
is inserted into selenocentric orbit. The rods are formed from prestressed
tape wound from a drum and passed through a drawplate. In contrast to the
~AE_F, insCalled on board the RAE-B satellite is an ejectable solid-fuel
rocket engine (thrust 80 kg, operating time 20 seconds) which brakes the
satell'ite in order to transfer it from the flight trajectory to the moon
178
' FOR OFFICIA;, USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFrICIAL USL ONLY
into :;elenocenrr.ic orbiC, and the ejer_table liqu:id-Luel engines (two -
= l i(Iuid-f'uC.l rocket engines with a thrust of 2.3 kg each and Cour spher.ical -
tanks wi.tli hydr.a�r.ine) cor.rect the flight trajectories on tlie "earth-moon"
path Ili1C1 1.f1 tiClE:l10C@11CC1C orbit.
_ "Lxpl.orer-50" (`I'aUle, No 12). Ttle tenth and last American satellite ot-
_ the I;�IP2 series (7M11-J, I igure 2) is designed to investigate radiati.on,
- cosmic rays, the solar wind, and magnetic and electric Lields. The satel-
- lite weighs 395 kg. In structural design and service equipment it is
, simi.iar to the IMP-FI satell.ite ("Explorer-47," see YEZHEGODNIK BSE, 1973, -
_ pp 529--30). The orbits of the "Explorer-50" and "Explorer-47" satel'lites =
almost coincide. The angular distance between the two satellites frequently _
- is close to 180 degrees. This offers the possibility of simultaneously
taking measurements at two points in space located on opposite sides of =
Ltie eartli. For example, it is possible simultaneously to investigate the -
eif.'e.cts of the solar flares on near-earth space on the day and night sides
= of the pl.anet. The first Ir1P satellite was launched in 1963. The ?MP-J ~
= satell.ite was ctesigned to function for a year. Thus, by the end of the _
_ operational service of the IMP-J satellite, the studies using the IMP
satellites would have encompassed the entire 11-year solar cycle (1963-
- 1974).
"Lxplorer-51" (Table, No 18). The first satellite in the AE series (AE-C, _
rigure 3) of the "second generation"3 tor comprehensive studies of the
- upper layers of the atmosphere at altitudes of 120 km and higher. The
= satellite weighs 660 kg, including 95 kg of scientific equipment and 170 kg _
~ of onboard hydrazine reserves for correcting the trajectory. The hull has _
~ the shape of a regular 16-sided prism (height 1.14 meters, transverse
dimensions 1.37 meters). The -10,000 solar elements mounted on the hull
_ pr.ovide a total power of 160 watts; for operation of the scientific instru- _
- ments, a power of 114 watts is required. In the electric power supply -
system, nickel-cadmium batteries are also used. In orbit the satellite
- can be oriented with respect to three axes (ori.entation precision one
- angLlar minute) or stabilized by rotation (one to ten rpm). The axis of
rotation must be perpendicular to the orbital plane. ~
- The scientific equipment module includes ultraviolet spectrometers for
- r.ecording solar radiation and radiation of the earth's atmosphere, a =
= photometer for recordi.ng the luminosity of the sky and the aurora polaris, _
- zi mass spectrometer and a spectrometer for determining the concentration
of neutral gases, an accelerometer for calculating atmospheric density ~
- with respect to decelerating the satellite, instruments for determining the -
ion and electron concentration in the atmosphere, and so on (a total of 14 -
instruments).
= 'I'lic satel].ite is inserted into ~ ini. tial orbit with a perigee of 156 km
and an apogee of 4,305 km. Duri.g the first five or six months, it must
be L-r.ansferred about five times to an orbit with a perigee of 180 km and,
alter- a f.ew days, returned to the initial orbit. These maneuvers as well as
= 179 -
- FOR OFFICIEw USE ONLY -
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
~ FOR OFFICIAL USE ONLY i
. ,
rhe compensation of rhe aerodynamic braking in the perigee of the initial !
and the low orbit are provided for by the onboard engine. When the
hydrazine reserve is almost completely exhausted (approximately six months
aFter the launch), the satellite mus*_ be moved to a circular orbit -300 km
- high which will not be corrected. According to calculations, the satellite ~
can stay in this orbit for approximately a year.
NOt1A-3 (Table, No 14). The next American NOAA meteorological satellite -
. (ITOS-r)4. The satellite weighs 340 kg. In str:ictural design and service
equipment the satellite is similar to the preceding ITOS satellites (see
YEZHEGODNIK BSE 1971, pp 503, 504, 507 and 1973, p 531). The same scien- _
tific instruments were installed on it as on the NOAA-2 satellite (ITOS-D).
j
= Transit (Table, No 13). The next satellite for use in the navigational
satellite system of the U.S. Air Force which is called NAVSAT.S The system ~
has been in operation since 1964. In recent years, five satellites have
- been used in it. On 29 October 1973 a satellite had to be launched to ;
replace one of the five system satellites in which the stabilization system ,
had failed (this satellite had operated since 1967). The operational model '
of the "Transit" satellite (see YEZHEGODNIK BSE 1964, pp 499, 500, 502)
weiglis -60 kg. Its hull (see Figure 4) is a multifaceted prism (height
30.5 cm, transverse dimension 45.7 cm). -
USCS-3 and nscs-4 (Tables, N(., 16 and 17). The second pair of satellites -
- of the DSCS-2 model for use in the improved military communications system
which must insure global continuous secret "strategic" and "tactical" -
communications (radio telephony, digital and video information transmission) -
with multistation access. The satellites weigh 558 kg each. They are an -
improved model of the DSCS-1 and DSCS-2 satellites (see YEZHEGODNIK BSE -
. 1972, p 521).
Meteorological Satellite (without a designation) of the U.S. Air Force (see
- Table, No 8).6 The next satellite for the meteorological data collection
system in the interests of the U.S. Air Force and Navy. For the normal -
functioning of this system, there must be two operating satellites in orbit
- at any given time. The system was created in 1966, after which satellites _
fiave been launched periodically to replace those which fail.
N-
_ 'L'he satellite weighs 195 kg. Its hull (see Figure 5) has the shape of a
12-sided truncated pyramid (height 1.64 meters, diameter of the large base "
1.3 meters, diameter of the small base 1.1 meter). Solar cells are mounted
on 11 out of the 12 faces of the hull; a turnstile antenna is mounted on
the remaining face. Louvers are provided in the thermal control system. _
The triaxial orientation system uses an induction coil which interacts with
_ the earth's magnetic field (bank, yaw) and a flywheel (pitch). In order to .
cietermine the earth's vertical, there is an infrared sensor. The output
- power of the onboard transmitter is 6 watts. The payload of the satellite
- is a four-channel radiometer built by Westinghouse and an eight-channel =
= radiometer built by Barnes Engineering. With the first radiometer, images
of the cloud cover were obtained during daytime and nighttime, both in the
180 -
FOR OFFICIA:. USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY -
_ visible and in the infrared ranges of the spectrum, but it is possible
- to OI)L'3111 imafies in the visible region of the spectrum at night only in
moonl.ight. 'I'wo channels operating in visible light (0.4-1.1 micron) -
- encompass the near inf.rared region which Fermits the clouds, the dry land -
and water surEace to be better clistinguished. The operating band of the
two infrare.d channel.s (8-13 microns) is selectcd with consideration for the =
f.act ttial they record cirrus clouds iahich can be transparent in visible
light. The two visible channels provide resolutions of 0.63 and 3.7 km; _
' the t-wo infrared channels provide resolution of 0.67 and 4.4 km. Using the ~
_ second radiometer (--15 microns), the vertical temperature profi.le of the
atmosphere is obtained.
In the Air I'orce meteorological system, stationary and mobile (transported
_ by air.craft) stations are used. The latter permit the troop soyedineniye
commanders to obtain meteorological data of a tactical nature directly from -
the satellites in real time. These data were used, in particular, when
planning the air operations in Vietnam.
Secret Satellites of the U.S. Air Force. No official information on the
desi.gnations and missions of the serret satellites has been published. ~
_ According to unofFicial information, the following types of secret satel-
- lites were inserted into orbit in 1973:
- 1. Two satellites for detailed photo reconnaissance (Table, No 4 and 11). -
For information on such satellites (see YEZHEGODNIK BSE 1973, p 534).
= The firsr of these satellites ceased to exist on 13 June 1973, and the
- second on 29 October 1973. According to the suggestions of some reviewers,
' these satellites were used not for detailed photographic reconnaissance,
~ but for testing experimental equipment which in the future is to be in-
sta].led on satellites for observation of the ocean. This equipment, it is -
assumed, includes instruments cahich operate both in visible and in infra- `
= red regions of the spectrum. According to calculations, the scanning camera
of the MSS type operating in the infrared part of the spectrum on the ERTS-1
satellite (see YEZHEGODNIK BSE 1973, p 531) would insure sufficient resolu- _
tion for observation of large military ships. The onboard computer of the
satellite could automatically identify ships by the characteristic emission
of the ship itself and its wake. Then it would be possible to decrease
- significantly the volume of information tru_.~iitted from the satellite to
earth.
2. '1'hree "Big Bird" satellites ("Big Bird-4, -S and -6," Table, No 2, 7
and 15) L-or surveying and detailed photo reconnaissance launched in
accordance wirh program 467. For information on these satellites see r
YE7.HEGODNIK BSE 1973, p 534). It is also reported that the Perkin-Elmer -
camera installed on the satellirQ for L.ztailed reconnaissance when sur- -
veying from an a]_titude of 60 kn insures resolution better than 0.3 meters.
- According to certain information, the camera is equipped with a 3-meter -
telescope. Six containers are used to return the film taken by this camera. _
When the satellite is in orbit for months, the contairers can be returned =
to tlle earth at intervals of 2 or 3 weeks. It is possible that the satellite. -
_ 181
FOR OTFIi,I!� USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
- equipment includes the television camera with a telephoto lens and variable
- focal LC'.I1};tfl, cameras Cor infrared photography and also a side scanning
rziclar (it iias been reported that the signals from this radar has been
- picked up by cer.tain telescopes). It is proposed that radio relays will
- later be installed on the "Big Bird" satellites to provide communications
between ground media and strategic aircraft in the polar regions.
The first of three "Big Bird" satellites launched in 1973 ceased to exist
, on 19 May 1973, and the second on 12 October 1973. The third continued to
= operate in 1974.
Figure 1. "Explorer-49" (RAE-B) Satellite
Key:
l. Onboard solid-fuel rocket engine
2. Dipole antenna rod
3. V-antenna rod (scale not m.:ir.tained)
4. Weight on the end of rod
5. Telemetry system antenna (a total of 4)
6. I.iquid-fuel engine
7. Solar panel (a total of 4)
182
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOh OFFICI:AI, iISE ONLY
Figure 2. "Explorer-50" (IMP-J) Satellite.
Figure 3. "Explorer-51" (AE-C) Satellite.
183
FOR OFI'ICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
Figure 4. Operating Model of the "Transit" Satellite (in the Last Stage
of the Booster Rocket with Builtin Solar Panels).
5 �
Figure S. U.S. Air Force Meteorological Satellite
184
FOR OFFICI.4; USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
roEi orFzcr.AL usI. oNl,Y
s
H
Figure 6. "riariner-10" Automatic Interplanetary Station. 1--Omnidirec-
tional antenna; 2--Device for investigating solar plasma;
3--Tri-axial indiiction magnetometers; 4--Sound protective
shields of the magnetometers; S--Set of sensors ("telescope")
for recording charged particles; 6--Ultraviolet spectrometer
on the hull of the station; 7--Heat insulation; 8--Solar panels
(reverse side); 9--Microengines for orientation with respect to
bank and yaw (on the ends of the panels 8); 10--Stellar sensor;
11--Reflector of the unidirectional antenna; 12--Microengines
for orientation with respect to pitch (on the hull of the station;
13--Radio transmitnr in the X band; 14--Sun sensor; 15--Scanning
platform; 16--Television cameras; 17--Ultraviolet spectrometer
on the scanning platform; -8--Inf.rared radiometer; 19--Station's
sun shield; 20--Lou �.rs for the thermal control system; 21--Solar
cells.
185
roR orrr.cr.t,L u~~ OiNLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
- 3. One IriEWS operational satellite (IMEWS-4, Table, No 6) for early detec-
tion of the launching of strategic satellites from ground launch sites and
from submarines, recording nuclear blasts as well as other missions of a
. military nature. For more information about the satellites launched in ac-
cordance with program 647, see the YEZHEGODNIK BSE, 1973, p 534. It has
been reported that the infrared sensors on the IMEWS satellites have gradu-
. ally begun to lose their sensitivity for an unexplained reason. It is pro-
_ posed that this is the result of nuclear blasts in the atmosphere by France
- and China.
- 4. One experimental BMEWS satellite (BMEWS-7, Table, No 1) for developing
equipment to detect strategic rocket launching. For more information on
these satellites see the YEZHEGODNIK BSE, 1973, pp 534, 535. It has been
_ proposed that the BMEWS satellites launched in recent times are being used
to discover why the infrared sensors on the IMEWS satellites have lost their
_ sensitivity sensors. It is also assumed that a new type of detectors are
being tested on the BMEWS satellites which will not only detect rocket
launchings but also track their nose cones in the middle part of the tra-
jectory, permitting calculation of the strike point.
- 5. The experimental satellite (Table, No 9) launched in accordance with
- program 711 for testing equipment and solving the technical problems of
- communications with strategic bombers on flights in polar regions. In con-
trast to all the remaining modern foreign communications satellites for
civilian and military purposes inserted into stationary or near stationary
orbit, this satellite is in an elliptic orbit with an inclination of 63.2
_ degrees. This orbit, in contrast to the stationary orbit, permits comm.uni-
cations coverage of the polar regions. The sharply elongated elliptic orbit
with the apogee over the northern hemisphere provides a prolonged visibility
zone for the users located there. This is the second such satellite launched
in the United States (for information about the first one, see the YEZHEGODNIK
_ BSE, 1972, p 529, Table, No 11).
"Anik-2" (Table, No 3). The second "Anik" communications satellite for the
commercial communications system servicing the territory of Canada. It was
- manufactured in the United States with the participation of Canadian compan-
= ies. It is completely like the "Anik-1" satellite (see the YEZHEGODNIK BSE,
= 1973, p 535). Several of the radio relays of the satellite are leased by
American companies for communications servicing of United States territory.
INTELSAT-E (Table, No 10). The fifth satellite of the INTELSAT-4 series for
= use intthe global commercial communications system. It was inserted into
- statio~zry orbit above the Atlantic Ocean where it plays the role of a re-
serve for the INTELSAT-4A and INTELSAT-4B satellites in operation there at
- the present time. The INTELSAT-4E satellite is completely like the previous-
ly launched satellites of the INTELSAT-4 series (see the YEZHEGODNIK BSE,
1972, p 525 and 1973, p 536).
186
- FOR OFFICIAL USE Oh'LY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
TpaNCnoptNwN
Kopa6nb 0p6wranbx3a ciaNUwe..CKaNn36'
1 2 0 3 4 5 6
go Om~
7
Figure 7. Basic components of the "Skylab" Station, including the "Apollo"
Transport Ship Docked with It (for the description see pp 532-533): 1--
Transport ship; 2--Docking unit; 3--ATT'I set of astronomical instruments;
4--Lock; S--Equipment compartment of the "Saturn-5" booster rocket struc-
turally entering into the composition of the station; 6--Station module.
Key: (A) Transport ship (B) "Skylab" orbital station
Automatic Interplanetary Stations
- At the beginning of December 1973, the "Pioneer-10" autom,atic interplanetary
station launched in 1972 completed its flight past Jupiter. On 6 April 1973,
the "Atlas-Centaur-Werner-2" booster rocket was used to launch the "Pioneer-
11" automatic interplanetary station for studies of Jupiter and Saturn from
= a fly-by trajectory. On 3 November 1973, the "Atlas-Centaur" booster rocket
was used to launch the "Mariner-10" automatic interplanetary station for
studying Venus and P[ercury from a fly-by trajectory.
,
"Pioneer-10." This station des gned for surveying and sounding Jupiter was
inserted into the flight trajectory to Jupiter on 3 March 1972 (see the
YEZHEGODNIK BSE 1973, pp 536, 537). On completing the flight by this tra-
_ jectory, on 15 February 1973 the station left the belt of asteroids between
the orbits of Mars and Jupiter.
187
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
- SttIdies on the interplanetary trajectory demonstrated that the concentration
- of ineteor particles - 1 micron in size diminishes on going away from the
suii, and at a distance of 3.5 astronomical units, that is, at the outer edge
- of the asteroid belt, it drops almost to zero. Contrary to expectations,
the concentration of particles 10 microns in size, which are the greatest
- danger to spacecraft, did not increase in the asteroid belt. There were al-
- most three times more particles 100-1,000 microns in size in the asteroid
belt than between the orbit of the earth and this belt. No particles greater
than 1,000 microns in size were detected by the onboard complex of "Sizif"
- optical telescopes designed to record asteroids and meteor bodies. The in-
- tensity of the solar magnetic field, the density of the solar wind and the
number of high-energy particles of solar origin decrease approximately pro-
= portiona.tely to the square of the distance Prom the sun. Aluminum and sodium
~ atoms were detected in the cosmic radiation for the first time. Helium atoms
_ which obviously belonged to the interstellar gas were recorded in the inter-
planetary medium.
The surveying of Jupiter (using a photopolarimeter) began on 4 November 1973.
- From 4 to 25 November, surveying sessions were held for 3 to 6 hours each
- day, and beginning on 25 November, round the clock.
On the photographs it is obvious that Jupiter is covered with concentric
- stripes of grey, orange, red brown, yellow and blue. The "red spot" which
has several points is clearly isolated. The outer edge of the spot are
sharply outlined and are darker than the inner part.
Picture of Jupiter taken by the "Pioneer-10" automatir_ interplanetary
station (the "red spot" and the shadow of the satellite Io on the surface
of the planet are visible).
- On 4 December at 0225 hours Greenwich time, the "Pioneer-10" automatic inter-
planetary station passed its minimum distance from Jupiter--131,000 km from
= the tops of the clouds or 2.85 times the radius from the center of the planet.
~ The automatic interplanetary station passed over the eastern or right hard
188
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
- FOR OFFICIAL USE ONLY
- (Cor the earth observer) limb of Jupiter and flew around the planet counter-
clockwise (if we consider from the direction of the north pole of the eclip-
~ tic), thaC is, with respect to rotation of the planet. The inclination of
= the bypass trajectory to the Jupiter equator was 14 degrees. Under the ef-
- fect of the gravitational field of the planet, the trajectory of the auto-
= matic interplanetary station was twisted almost at a right angle and the
automatic interplanetary station began to move along the tangent to the
orbit of Jupiter.
At 0239 hours on 4 December the automatic interplanetary station passed
behind the Jupiter satellite Io (the cover lasted 91 seconds) and then it
- set behind Jupiter (the cover lasted 64 minutes) and flew in the shadow of
� Jupiter (for 50 minutes).
According to calculations, continuing its flight, the automatic interplane-
tary station will intersect the orbit of Saturn in 1976, the orbit of Uranus
in 1979, the orbit of Neptune in 1983 and the orbit of Pluto in 1987. It is
hoped that communications caith the automatic interplanetary station will be
maintained approximately until 1978 (to the time that it is approximately
3 billion km from the earth).
- Some highly preliminary results of the study of Jupiter, its satellites and
_ tiear-planetary space using the instruments of the "Pioneer-10" automatic
~ interplanetary station are presented below.
The magnetometer showed that the axis of the magnetic field of Jupi-ter is
- inclined 15 degrees to the axis of rotation of the planet. The source of
the magnetic field is asymmetric with respect to the center of the planet
and is somewhat shifted toward the north from the equatorial plane. The
- intensity of the magnetic field on the surface of the planet is defined as
- 4 gauss. The most important discovery is the strong concentration of cap-
tured radiation around the plane of the magnetic equator of Jupiter (see the
- figure). In the opinion of some scientists, in the magnetosphere of this
planet other electrodynamic processes are more decisive than in the magneto-
sptiere of the earth. The radiation concentration in a limited zone explains
- the fact that the intensity levels of tre fields and particles recorded by
- the instruments of the automatic interplanetary station varied with a 10-
= hour period. Obviously, as a result of the inclination of the magnetic axis
to the axis of rotation of the planet, the equatorial peak intensity passed
- through the automatic interplanetary station approximately synchronously
with the period oE rotation of the planet around its axis (10 hours). The
radiation concentration is an important factor for planning future flights,
in particular, the flight path of the "Pioneer-11" automatic interplanetary
- station past Jupiter. The interplanetary stations can approach relatively
- close to the planet, passing rl,e equa~orial zone and at the same time with-
out subjecting the onboard equ pment to the danger of radiation damage.
i
189
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
- Radiation detectors demonstrated that in a zone extending 35 degrees from
the center of Jupiter, the fields and particles rotate with the same ve-
locity as the planets. The energy of the captured particles is especially
high in the 10 degree zone. At a distance of 3 radii, the electron flux
= with an energy of more than 3 Mev is 5�108 particles/cm2-sec, the proton
flux with an energy of more than 30 Mev is 4�106 particles/cm2-sec. The
automatic interplanetary station received a radiation dose of approximately
500,000 rad (at the critical limit for some onboard equipment).
- o
The ultraviolet spectrometer recorded the Lyman-alpha hydrogen line (1216 A)
_ and the corresponding helium line (584 X). The presence of helium on Jupiter
was detected for the first time, although it had been theoretically pre-
dicted earlier. The ratio of hydrogen to helium still has not been cal-
culated for this is a very difficult problem.
By using an infrared radiometer in the ranges of 20 and 40 microns, the
. temperature distribution over the disc of the planet was obtained. The
- total thermal flux from Jupiter exceeds by 2.5 times the energy obtained by
_ the planet from the sun. In the opinion of a number of scientists, the planet
obviously is still passing through the stage of gravitational compression
in which the potential energy is converted to thermal energy.
Radio sounding when the automatic interplanetary station set behind the
planet demonstrated that it has a multilayered ionosphere.
_ Celestial mechanical studies by the trajectory measurements gave the fol- 3
lowing preliminary values for the density of the Jupiter satellites (in g/cm
' Io 3.48, Europa 3.07, Ganymede 2635, and Callisto 2500. A characteristic
feature is noted: the farther the satellite is from Jupiter, the smaller
its density. The mass of Jupiter only very insignificantly exceeds the
= value determined by ground observations. According to the trajectory meas-
, urement data, it was calculated that the ratio of the mass of the sun to'the
- mass of Jupiter is 1047.341. The compression of the planet on the basis of
= these data was defined as 0.065.
(5) vn3aNap (6 )
- Marnww,Lhrp;i MarxNronay3a ar.nNa
C~n~e~N6i~i/ 7
eP~tP \ )
_ ~ qM U`
TPaeKropNa
Marnnrnaa ocb" ~Ucb apaweHNn y
(2) (3)
- Magnetosphere of Jupiter, according to the data of the "Pioneer-II" Automatic
Interplanetary Station.
[Key on following page]
190
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007102/08: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
[Key for figure on preceding page]
(1) magnetosphere (4) automatic interplanetary (6) shock waves
(2) magnetic axis station trajectory (7) solar wind
- (3) axis of rotation (5) magnetopause
The meteor particle detectors have demonstrated that their density on Jupiter
is 300 times higher than in interplanetary space: of the interplanetary
trajectory the particles were recorded on the average every 600 hours; when
i, flying past Jupiter, every two hours.
"Pioneer-11." The basic missions of this station were to study the magnetic
field of Jupiter and its radiLtion belts, to investigate the heat balance
and the temperature distribution in the outer atmosphere of the planet, to
obtain images of the planet and some of its satellites in visible light,
more precisely to define the ephemeris and mass of the planet. On the flight
_ trajectory to Jupiter and after flight past the planet, provision was made
for studying the solar wind, the interplanetary magnetic field, cosmic radia-
tion as well as the meteor material in the asteroid belt for the first time.
- The station must fly past Jupiter on 2 December 1974 at a distance of about
42,000 km and under the effect of the gravity of this planet go into the
trajectory toward Saturn. The flight past this planet will take place in
October 1979.
� The "Pioneer-11" automatic interplanetary station weighs 258.5 kg, includ-
ing 30 kg of scientific instruments. In its structural design and service
and scientific equipment, the "Pioneer-11" automatic interplanetary station
- is similar to the "Pioneer-10" automatic interplanetary station (see the
YEZHEGODNIK BSE, 1973, pp 536, 537), but an induction magnetometer is also
- installed on 4-t to measure the intense magnetic fields near Jupiter (the
- measurement range of the instrument is up to 106 gammas).
"rlariner-10." The basic missions of this station are to survey and sound
Venus and Mercury from flight trajectory (in the gravitational field of
, Venus the station will complete a perturbation maneuver and transfer to the
_ flight path to Mercury). By using the television cameras of the station it
' is proposed that 5,700 picture of Venus and N 2,740 pictures of Mercury
will be obtained. Special attention has been given to the studies of Mer-
= cury: in addition to the survey, provision has been made for measuz'ing the
thermal radiation of the surface, the search for hot sections, determining
- the composition of the planet's atmosphere if it exists, the search for the
_ magnetosphere, recording '.he shockwave and particles captured by the mag-
netic field of the planet, the "tail" of the magnetosphe:�e, more precisely
calculating the mass and radiu: of r:ercury as well as t?.ie harmonics of the
gravitational field of the planet.
191
- FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
The "iltariner-10" automatic interplanetary station (see Figure 6) weighs
526 kg, including 77 kg of scientific instruments. The hull has the shape
of an octahedral prism (transverse dimension 1.3 meters). The solar panels
are 8 meters long. The thermal control system uses heaters, louvers, heat
shielding made of "beta" fiberglass, thermal insulation as well as a sun
shield of "beta" fiberglass and capton film with aluminuni coating. This
shield is needed because the trajectory of the station passes very close to _
the sun. Sun sensors, a stellar sensor which locks on Canopus or Vega and
gyrostabilized plat.-orm are used in the orientation system, and two (one
spare) sets of 6 microengines operating on compressed gas are used as the
servoelements. The precision of the orientation with respect to pitch and
yaw is 0.25 degrees. The nitrogen reserve for the microengines is 3.6 kg.
Four solar panels (total area 5.25 m2) provide a power of 475 watts when
flying past Mercury. In order to prevent heating of the solar cells above
100 degrees C on approaching the sun, the panels gradually rotate with re- _
spect to the longitudinal axis until they establish an angle of 70 degrees
to the direction of the sun. Before unfurling the panels and also during
the traiectory corrections when the panels are not turned towards the sun,
the electric power is provided by a storage battery. An S-band receiver,
two (or one spare) S-band transmitters (2113 megahertz) and an X-band trans-
mitter (II415 megahertz) have been installed on the station. The omnidirec-
tional antenna of the station operates in the S-band; the highly directional
rotating antenna operates both in the S-band (amplification factor 28 db)
- and in the X-band (38.5 db). The sharply directional antenna has a reflec-
tor 1.37 meters in diameter which is on a rod 1 meter long. The formation _
content when transmitting television images is up to 117,600 bits/sec, the
telemetry information is up to 2,450 bits/sec. The capacity of the onboard
memory is 1.6x108 bits. The correcting engine (thrust 23 kg) operates on
the products of the breakdown of hydrazine, the reserve of which is 27.2 kg
an3 insures a total increase of velocity of 115 m/sec.
The scientific equipment includes two identical television cameras each with
a telephoto lens (focal length 1,500 mm, viewing angle 0.5 degrees) and a
wide-angle lens (68 mm, 11-14 degrees). The survey is made in the visible
and ultraviolet ranges. The latter is especially important for obtaining
images of the cloud cover of Venus. The cameras are installed on a scanning
platform which can rotate with respect to two axes (255 degrees with respect
to one and +58 degrees to -180 degrees with respect to the other). One
- ultraviolet spectrometer is installed on the same platform, and a second one
is mounted on the hull of the station. In addition, an infrared radiometer,
a solar plasma detector that includes a scanning spectrometer and a scanning
electrostatic analyzer as well as a set ("telescope") of Geiger-Mueller
counters for recording charged particles are mounted on the hull. Tao magne-
tometers are placed on a rod 7 meters long.
The "Mariner-10" station was launched on 3 November 1973, and it was inserted
in the flight trajectory to Venus. In the near-earth segment, the onboard
television cameras were used to obtain several hundred pictures of the earth
and rhe moon basically to calibrate the cameras. On 13 November 1973, the
192
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OI'FICIAL USE ONLY
first correction was made to the trajectory of the station on the "Earth-
Ver.::s" Elight path; on 21 January 1974, a second correction was made. The ~ station flew past Venus on 5 February and Mercury on 29 riarch 1974. The
correction to the helioczntric orbit of the station after the f irst pass
near Mercury provided for a repeated pass near this planet on 21 September
1974 at a distance of 50,000 km.
Oroital Station and Manner Transport Ships
The "Skylab" orbital station (unmanned) was launched in 1973 in the United
States. Three crews of three astronauts each were delivered to it by the
"Apollo" manned transport ships. The first crew spent 28 days in the station
(from 25 i-fay to 22 June); the second crew spent 59 days (from 28 July to
25 September), and the third and last crew spent 84 days (from 16 rlovember
1973 to 8 February 1974). The basic missions of the "Skylab" program were
to study the effect of prolonged weightlessness on the physical coiidition _
and fitness ef the astronauts, medical experiments, observations of the sun,
studies oF the earth's natural resources, technological experiments, testing
various equipment and a number of other studies and experiments. The "Sky-
~ lab" station is experimental. It was proposed that it could be used to ob-
tain information important for the creation in t.he future of long-term manned
orbital stations as well as tor future prolonged manned flights to the planets.
On launching from the earth the "Skylab" station weighs 88.9 tons; in orbit
(after separation of the ejectable section of the nose cone) it weighs 77.1
tons. The length of the station in orbit is N 25 meters. It is made up of
the following basic components (see Figure 7, page 529):
1. A station module (14.66 meters long, 6.6 meters in diameter, a sealed
volume of 292 m3 weighing 35.38 tons with artificial atmosphere). The module
was created on the basis of the S-4V rocket developed in its time as the third
stage of the "Saturn-1B" and "Saturn-5" booster rockets. The hydrogen tank
- of the rocket (Figure 8, see page 529) has been partitioned into two com-
partments: the living quarters and laboratory. In the living quarters there
are four areas partitioned off: for sleeping, for personnel hygiene, for
leisure, the preparation and eating of food, for setting up and conducting
experiments. The oxygen tank of the rocket (volume 80 m3) is evacuated and
is used to collect waste which is discharged into it from the living quarters
through a lock.
2. The air-lock module (536 meters; 1.6-3.0 meters; 17.4 m 3 ; 22.2 tons).
A hatch for exiting to open space is located in it. Many units of the life-
support system and storage batteries are placed inside the lock. The oxygen
and nitrogen storage tanks are placed on the outside.
~
3. The docking adapter (5.27 1 :ters; 3.0 meters; 32.3 m'; 6.26 tons). It
is equipped with two berrhs with docking units. The axial berth is the basic
one, and the side berth, L.:e spare. The docking adapter has control panels
for the set of ATM astronomical instruments for observations of the sun and
the EREP instrument set for studying the earth's natural resources. The EREP
instruments are placed inside and outside the doclcing adapter.
193
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
Figure 8. Diagram of the Station Module (for the description see pp 532-
533): 1--Hatch; 2--coolers, freezers, and uncooled containers for food
products in the laboratory compartment; 3--fan in the personal hygiene faci-
lities; 4--bracket for fastening the solar panel; 5--sleeping cubicle in
the living qtiar.ters; 6--Facility for personal hygiene; 7--facility for leisure
time, preparation and eating of food; 8--lock for discharging waste; 9--grid
holding back solid waste; 10--evacuated tank for collecting waste;.ll--radia-
tor; 12--facility for setting up and conducting experiments; 13--water tanks;
14--storage; 15--air duct; 16--storage for film; 17--lock for putting scien-
tific equipment into ouzer space; 18--tanks with compressed nitrogen for the
TACS orientation system engines.
4. The set of ATM astronomical instruments (4.4 meters; 3.3 me~.ers; 11.8
meters). It is placed on a girder type struFture which is titled by 90
degrees after the station goes into orbit. In addition to th.e astronomical
instruments, the set includes onboard digital computers, power gyroscopes of
the orientation system, four out of the six solar panels, storage batteries
and a number of other units of the station service systems.
The life support system of the station is designed to create an oxygen- ~
nitrogen atmosphere (74 percent oxygen and 2.6 percent nitrogen) at a pres- '
sure of 0.35 kg/cm2. The comfortable air temperzture is 21+5� C. The onboard ~
oxygen reserve when launching the station was 2.23 tons, and the nitrogen ~
194 i
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL U5E ONLY
reserve was 0.6 tons (not considering the nitrogen reserve for the TACS
orientation system engines), there were 2.7 tons of water and 0.67 tons of
food products. All of the consumable materials were calculated to maintain
three crews in the station for a total of 140 days.
The thermal control system uses a liquid cooling system where the coolant
circulates, giving off heat in a radiator, heating elements, special paint
and thermal insulation. A decisive role in the thermal control system must
he played by the meteor shield surrounding the station module. It is made
up of aluminum alloy panels 0.6 mm thick which are pressed against the hull
in rhe remote section and, after the station goes into orbit, are moved 12
cm away from it.
The electric power supply system uses two solar panels on the station module
and four panels on the ATr1 complex. The size of the panels on the station
module is ti 30 meters, the tntal a-rea is 110 m2, the guaranteed average power
was no less than 3,800 watts, the peak power was 11,900 watts. Eight stor- _
age batteries in the air-lock module were charged from the solar cells of
these panels. The capacity of each battery was 33 amp-hours. They can pro-
vide a power of 3,830 watts in one orbit. The size of the panels on the ATM
complex is also , 30 meters. The total area is 110 m2, and the guaranteed
average power is no less than 3,700 watts. The peak power is 10,500 watts.
Eighteen storage batteries in the ATM set are charged from the solar cells
of these panels. The capacity of eacn battery is 20 amp-hours. They can
provide 3,700 watts of power in one orbit. Provision is made for the possi-
bility of transferring power between the electric power supply systems of
the station, the ATM set and the "Apollo" transport ship when it is docked
to the station.
The station has three orientation and stabilization systems: TACS, CriG and
EPC. The TACS system is used to keep the station quiet and provide initial
orientation, and later it is used only in the case of saturation of the power
gyroscopes of the CMG system. The TACS system operates both on command from
on board and on command from the earth. As servoelements the system uses
- six motors of 68 kg each operating on compressed nitrogen which is stored
under a pressure of 218 kg/cm2 in 15 spherical tanks mounted by a ring on
the rear of the station module. The total nitrogen storage (-+4.4 m3) for
the engines of the TACS system provides a total impulse of 27 ton/seconds.
The CMG system is used to stabilize the station in a given position with a
precision of 3'. The system uses a sun sensor, a stellai sensor and high-
speed gyroscopes, and as actuators it uses three power gyroscopes operating
from an asynchronous motor. The weight of each power gyroscope is 189 kg,
the rotor weight is 65.8 kg, the rotor diameter is 0.56 meters, the speed
is 9,100 rpm. The EPC system provides for aiming the astronomical instru-
ments of the ATri set at the selected scction of the solar disc or at another
heavenly body with the precisioi. of +?..S". The system uses sun sensors and
precision gyroscopes, and it uses electric engines as the actuators.
195
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
The interaction of three orientation systems and also the solution of a num-
ber of other problems are provided by two onboard digital computers (one
reserve) in the ATM complex. Each digital computer weights 44 kg, the over-
all dimensions are 19x48x77 cm, the intake power is 165 watts, the memory
capacity is 16,000 16-bit words, the reference time is 2.5 microseconds,
and the average speed is 60,000 operations per second.
The radiotechnical system includes a large number of receivers and transmit-
ters in the meL-er and decimeter bands for communications with the earth and
also radio teletype by which instructions to the astronauts and various in-
formation are transmitted on board. The transmissioii ;f television from on
board is provided by the radio technical system of the "Apollo" transport
ship docked to the station. Means of intrastation communications, devices
for video recording and memories for storing information from the scientific
instruments are provided. The radio technical system includes the transponder
and the meter band used in combination with the range meter on the "Apollo"
transport ship when rendezvousing in orbit.
The payload of the "Skylab" station includes the astronomical instruments
of *_he ATM complex, the instruments of the EREP complex for studying natural
resources, a number of devices for medical experiments, the means for con-
ducting technological experiments and also several dozens of other instru-
ments, devices and means for conducting the most varied studies. In addition,
on the "Apollo" transport ship when delivering the crew to the station, there
were various biological subjects for studying the effect of weightlessness
on them. The ATM complex includes a coronograph, an x-ray spectrograph,
spectroheliometer, an x-ray telescope, an ultraviolet x-ray spectroheliograph,
an ultraviolet spectrograph and two telescopes for observing the sun in the
H-alpha line. The EREP,complex includes six frame television camerasy a
topographic camera, an infrared spectrometer, a multirange scanning televi-
sion camera, a microwave sonde and the L-band radiometer. In order to con-
duct medical experiments, in particular., a bicycle ergometer, a device for
creating negative pressure on the lower half of the body, a rotating coulo-
metric chair, a scale, a treadmill, and so on are provided. In order to
perform technological experiments, a spherical chamber (0.4 meters in diame-
ter) with a cathode-ray gun and an electric furnace are used.
- The "Apollo" transport ship is a modified basic unit of the "Apollo" lunar
spacecraft (the command module, see the YEZHEGODNIK BSE, 1968, page 519).
The rated launching weight of the transport ship is - 14 tons; it is 11
meters long; and the diameter is 3.9 meters. The maximum weight of the pay-
load (not considering thp astronauts) delivered to the station by the trans-
port ship is 880 kg; the maximum payload returned in the transport ship to
Earth is 900 kg.
The proposed program provided for launching the unmanned "Skylab" station
on 14 May 1973 by the two-stage "Saturn-5" bocster roctcet into a circular
orbit 435 km high with an inclination of 50 degrees. On the naxt day,
15 May, the "Saturn-1B" booster rocket launched the transport ship with the
first crew, which stayed 28 days on the station and returned in the same
196
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OI'FICIAL USE ONLY
;
transport ship to Earth. It was proposed that the second creio be delivered
; to the station on 25 July, and the third on 26 October 1973. These two
crews were to stay 56 days on the station. In the interval between run-
ning the station, and after the third crew left the station, it was to be
, used for conducting certain experiments in the automatic mode by command .
from the earth.
Launching the "Skylab" statien. The "Skylab" station (unmanned) was launched
by the two-stage "Saturn-5" booster rocket on 14 May 1973, and it was in-
serted into orbit with a perigee of 434 km, an apogee of 437 km and an in-
clination ot,50 degrees. The orbital period was 93.2 minutes. The mass of
the object inserted into orbit (the station and the second stage of the
booster rocket with residual fuel) was 112 tons. In the insErtian segment
a 63 second flight, the meY.eor shield surrosnding rhe station module was
broken under the effect of dynamic pressure. This shield, as was discovered
later, was not tight enough against the hull. The broken shield damaged the
coupling of one of the two solar panels to the hull (panel No 2) of the
station module. In orbit, ugon separation of the second st.ge from the sta-
tion, the exhaust of the braking engines of the stage broke panel No 2. The
second panel (panel No 1) on the station module opened ozly partially: it
was wedged by a piece of the meteor shield. There was no other damage to
the station.
The four solar panels of the ATM complex remained the only sources of elec-
tric power, providing only half the calculated power. Under these condi-
J tions, it was still yussible to perform part of the planned studies under
a highly abbreviated program and with the required use of the batteries of
- the hdryogen-oxygen fuel elements of the transport ship to power the sta-
tion equipment.
A more serious problem than the shortage of electric power was the absence
of the meteor shield, wliich plays an important role in the heat regulating
system of the station: on 15 May the temperature in some of the compart-
ments of the living quarters had already risen to 38�C, and the temperature
of a number of sections of the outer wall was up to 82�C. On 16 May the
temperature rose to 65.6�C and 163�, respectively. The heating was danger-
ous for the electronic equipment, the film, food and medicines on boar.d.
In addition, at high temperature some of the plastic materials inside the
station could give off toxic gases. In order to decrease the concentration
of such gases, the air in the station facilities was periodically purged,
and the quarters were again filled with oxygen and nitrogen.
In order to decrease the overheating, it was decided to change somewhat the
station's regular "solar-inertial" orientation in which the longitudinal
axis is perpendicular to the directio:, of the sun and certain sections of
the hull are constantly exposek to solar rays. After a number of tests,
the orientation in which the longitudinal axis of the station was at an
angle of 40 degrees to the direction of the sun was recognized as the most
expedient. Thus, the angle of incidence of the solar rays on the hottest
197
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
sections was diminished, but other sections began to overcool. The later
was no less dangerous than the superheating: a temperature drop below 0�C
could lead to freezing of the water in the tanks and lines and destruction
of them. By again changing the orientation, it was possible to grevent the
temperature from dropping below 2.8 degrees. The orientation of the sta-
tion had to be changed many times, "balancing on the hot wire," which led
to the high consumption of the compressed nitrogen for the TACS system
engines.
The launching of the transport ship with the first crew to the station was
delayed from 15 May first to 20 May and then to 25 May (launches were pos-
, sible every 5 days when the path of the station passed over Cape Canaveral).
1"t was decided that the astronauts could take several emergency heat shields
and, depending on the circumstances, install one of them to replace the
broken meteor shield inasmuch as there was no other way of restoring a com-
~i fortable temperature on the station. The astronauts took with them certain
~ instruments to try to open the partially open panel No 1 all the way.
The "Apollo" No 116 transport ship with the first station crew was launched
- on 25 May 1973 by the "Saturn-1B" booster rocket. The first crew included
Charles Contrad (commander), Joseph Kerwin (physician) and Paul Weitz (co-
' pilot). Only Conred had experience with space flight (on the "Gemini-5" and
"Gemini-11" satellites and also on the "Apollo-12" spacecraft as commander
of the second American lunar expedition). The weight of the transport ship
~ into which the equipment was loaded to repair the station reached 14.19 tons.
The booster rocket inserted Che transport ship into an initial orbit wiCh
an apogee of 352 km, a perigee of 156 lan and an inclination of 50 degrees
(the calculated values of 350 lan, 150 lan and 50 degrees). As a result of
six maneuvers, at 7 hours 40 minutes after launch the transport ship rendez-
voused with the station. The astronauts began to fly around it for inspec-
tion and examination of the damage. An effort was made to open panel No 1.
For this purpose, Weitz, hanging with his shoulders out of the hatch of the
transport ship manipulated a hook on a long handle and Conrad held the tr;ns-
port ship at a distance of one or two meters from the panel. The effort did
not succeed.
The transport ship was docked with the station 15 hours 52 minutes after
launch only on the lOth attempt. After the ninth unsuccessful attempt the
astronauts unsealedthe cabin of the transport ship and examined the dock-
ing unit where a short circuit was detected in one of the electric circuits.
The short circuit was bypassed by using a connecting cable.
On 26 May, the astronauts in gas masks and with toxic gas d'etectors moved
from the transport ship to the station. The detectors found no toxic gases.
The temperature in some of the station facilities had reached 55 degrees.
First the astronauts installed the heat shields. The "umbrella" was selected
from among the three shields taken with them (an "umbrella," a"canopy" and
a"sail"). It was extended from the station on a rod through the airlock
198
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
for putting the scientific equipment out in space, and it was opened by
springs, although partially. The temperature in the station almost im-
mediately began to drop (by approximately 0.5 degrees per hour). On 27 May
the astronauts began to activate the station.
On 28 May the crew proceeded with the scientific program; in particular, the
, astronaut Doctor Kerwin began regular medical examinations of his colleagues
and himself. On 29 rlay the first observations of the sun were made using
the ATM complex and the first studies were made of natural resources using
the EREP complex. On 31 May during the next session of the study of natural
resources, there were failures immediately in several of the storage bat-
teries of the ATri complex, which further compiicated the critical situation
with respect to electrical power. The scientific program, in particular the
study of natural resources, had to be curtailed. The decision was made on
7 June to go out into open space and repeat the effort to open panel No 1,
this time using shears which were available among the repair tools on the
station to cut the metal.
Conrad and Kerwin participated in the 7 June walk which lasted 4 hours 15
minutes. Conrad, holding onto an improvised railing, moved along the hull
of the station to panel No l. Using the scissors, the fragment that had
jammed the panel was cut away, and the panel was freed. After a few hours
it opened completely and provided a power of apnroximately 3,000 watts, and
together with the panels of the ATM complex, 6,500 to 7,000 watts. The
"energy crisis" in the statiori was over.
Beginning on 9 June, the operations of the station developed in accordance
with the complete program. Even on the free days provided by the schedule,
the astronauts refrained from rest.
On 19 June, the second and last walk of the astronauts of the first crew
into open sgace took place basically to replace the film holders in the ATM
complex. Conrad and Weitz participated in the walk which lasted 1 hour 36
minutes.
On 22 June the astronauts returned to the earth in the transport ship. The
flight lasted 28 days 000 hours SO minutes. The crew compartment with the
astronauts was lifted to the deck of the "Ticonderoga" aircraft carrier, and
the crew members independently stepped out of the compartment onto the deck.
Conrade had lost 1.7 kg of weight, Kerwin 2.9 kg, and Weitz 3.7 kg. The
calf muscles in ali three had shrunk by approximately 2.5 cm.
The flight of the first crew of the "Skylab" station was characterized by
unexpectedly fast and sickness-free adaptation of the astronauts to the
condition of weightlessness an(' compaiatively easy readaptation to the earth's
gravitational conditions especa'.lly Eor Conrad. Obviously the latter was
promoted by the regular, long exercises on the bicycle during the flight.
In spite of the fact that the first crew was forced to devote a great deal
of time to repair operations, the flight program was approximately 80 per-
cent completed, including the medical experiments--90 percent; so],ar
199
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR QFFICIAL USE ONLY
Kerwin examining Conrad's oral cavity.
"Skylab" station in orbit (the arrow indicates the broken wires at the place
where the No 2 panel was torn 3way). The picture was made from the trans-
port ship after rendezvous with the station.
observations--81 percent; studies of natural resources--88 percent. Using
the ATM complex. 30,200 photograph were taken, and with the EREP, 16,700
photographs and 13,700 meters of magnetic tape recordings.
The "Apollo" No 117 transport ship with the second crew for the station was
launched on 28 July 1973 using the "Saturn-1B" booster rocket. The second
crew included Allen Bean (commander), Owen Garriott (scientist and astro-
naut) and Jack Lousma (copilot). Only Bean had had spaceflight experience
(on the "Apo11o-12" spacecraft when he landed on the Moon together with
Charles Conrad). The transport ship weighed 14.2 tons, including 862
tons of payload (the equipment for repairing the station and performing
various experiments). The equipment for repair included a new "umbrella"
shield (it was not required), a set of six spare gyroscoges, a spare heat
exchanger, a television monitor and two tape memories. The equipment for
the experiments included an aquarium with two gudgeons and 50 gudgeon eggs,
a cage with two spiders, containers with drosophila and mice, and so on.
200
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
o,
FOR OFFICIAL USE ONLY
Provision was made far the study of the eftect of weightlessness on the
state and the behavior of these biological subjects.
_ The booster rocket inserted the transport ship into the initial orbit with
a perigee of 155 km, an apogee of 232 km and an inclination of 50 degrees.
As a result of nine corrections, the transport ship rendezvoused with the
station and 8 hours 29 minutes after launch, it docked with it on the first
attempt. During insertion, a leak occurred in one of the four auxiliary
engine blocks of the transport ship, and this block was shut down.
' During the first days at the station all three crew members experienced
severe motion sickness symptoms; they frequently could not eat; their physi-
cal fitness declined, and the station was demothballed significantly behind
schedule. The first walk in open space planned for 31 July was put off un-
til the astronauts felt better.
On 1 August the scientific experimentation began. The observations of the
fish demonstrated that they had lost orientation: they swam in a spiral
head down in the aquarium. Later, when the young fish were hatched from
the eggs, no disorientation was observed. During the return to earth, the
fish died so that it was not possible to study their readaptation to gravi-
tational conditions. The first spider forced into the container where he
cou.ld spin a web initially spun it randomly in the corners of the container,
but then he created a web of proper geoma;;ric shape. Later, the same thing
occurred with the second spider. Initially no provision had been made to
feed the spiders in flight, but later the decision was made to feed them
so as to return them live to the Earth and study the readaptation process.
The spiders gradually learned to eat pieces of beefsteak. However, the
spiders did not survive. One of them died in flight, and the other during
return to earth. The drosophila and mice died as a result of equipment fail-
ures.
- Oci 2 August a leak was detected in the oxygen unit in one of the auxiliary -
engine blocks of the transport ship. Even the p�roblem of expediency of an _
emergency return of the astronauts to rhe eartr was considered while the
rPmaining two modules functioned. Then it was decided that this was not
necessary inasmuch as the astronauts were not threatened with any immediate
danger. In case the remaining auxiliary engine blocks failed, which would
make it impossible to use the No 117 transport ship docked to the station
- to return the astronauts to Earth, the preparation of the booster rocket
with No 118 transport ship would have been accelerated to deliver a third
crew to the station in case it was necessary to use this spacecraft as a
rescue vehicle for emergency evacuation of the astronauts. In this case
two additional chairs would have been installed in the No 118 transport ship, -
and the crew would have been reduced from 3 to 2: the three free chairs
would have been planned for thk astronauts evacuated from the station. The
two remaining auxiliary engine olock of the No 117 transport ship docked to
the station remained fit until it was time for the second crew to leave the
station, and it was not necessary to launch the rescue ship.
201
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
The first walk in open space was on 6 August when the disorientation symp-
toms ceased altogether.in the astronauts. The walk lasted 6 hours 31 minutes,
and it was performed by Garriott and Lousma. Their basic mission was to
install the second heat shielding mechanism ("canopy") above the umbrella
sh:ield opened by the first crew which, first of all, had not opened fully
and which, secondly, under the effect of the sun's ultraviolet radiation had
begun to lose its heat protective properties. In order to install the "cano-
py" shield:the astronauts needed 4 hours, twice the calculated time. In
addition, they replaced film holders in the ATM astronomical instrument
complex.
i
.
.

�
~
Garriott at the control panel of the A.TM complex
"Skylab" Station after Unfolding Panel No 1(Panel No 1 and the umbrella
shield are visible). The picture was taken from the transport after un-
docking from the station.
202
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
P'OR OFFICIAL USE ONLY
Beginning on 7 August, tlie astronauts set about doing the scientiEic research
in accordance with the complete program. The basic mission of the second
^rew was observation of the sun using the ATM complex. In spite of the qiliet
period of the solar cycle, the activity of the sun was unexpecredly high,
which made these observations especially valuable. In addition to them,
studies were made of the natural resources of the earth, and medical experi-
ments were carried out as well as meteorological observations, cests (in the
laboratory compartment of the station) of several types of units for travel
in open space, technological experiments and so on. The fitness of the
astronauts reached a very high level, exceeding the planned fitness by al-
most 50 percent. The crew members, overcome by the enthusiasm of the re-
searchers, gave up their rest time provided for by the schedule and per-
sistently asked ground control to develop additional experiments for them.
-
On 24 August a second walk in open space took place, the basic mission of
I which was the connection of a cable to the hull of the docking structure and
to the split in the ATM complex. This cable joined the spare gyroscopes in-
stalled by rhe astronauts in the docking structure and the digital computer
in the ATri complex. The basic missions of the space walk were replacement
of the film holders in the ATM complex and ;ome small repair operations.
The CVA was made by Garriott and Lousma and it lasted for 4 hours 21 minutes.
On 25 August, the second crew bro ke the space flight time recard which be-
longed to the first crew of the "Skylab" station. Then on the basis of the
results of the medical examination, the astronauts were given permission to
stay in space for another week. Initially it was planned that the second
crew would spend 56 days at the station; then the time was increased to 59
days, cohich made it possible to land the astronauts returning from the sta-
tion in the Pacific Ocean closer to the coast of the United States (350 km
instead of 1,930 km fron San Diego and western California), and, likewise,
to deliver the crew faster to the Johnson Center in Houston, where the most
refined equipment exists for complete medical examination and to give medi-
cal aid if this turns out to be necessary.
On 22 September, the third and last EVA of the astronauts of the second crew
took place, basically to replace the film holders in the ATM complex. Bean
and Garriott participated in the walk lasting 2 hours 49 minutes.
Lousma testing the space walk equipment.
203
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
On 25 September, the astronauts returned to earth in the transport ship.
The flight lasted 59 days 11 hours 9 minutes. The crew compartment with
the astronauts was lifted onto the "New Orleans" helicopter carrier. Bean,
Lousma, and Garriott stepped independently from the capsule to the deck.
The astronauts lost 3.2 to 3.6 kg of weight each. Their condition after
returring to the earth was better than the medical specialists expected
and better than the condition of the members of the first crew (including
Conrad).
The second crew astronauts overfulfilled the flight program by approximately
50 percent. Observations of the sun using the ATM complex were made for
305 hours (instead of 205 hours according to plan). During this time
77,600 photographs were obtained, in particular, photographs of more than
100 flares and large protuberances (21 August). The EREP complex was used
for 39 study sessions of natural resources instead of 26 according to plan;
16,800 pictures and 29 km of magnetic tape recordings were obtained. The
members of the second crew performed 12 unplanned experiments.
The "Apollo" No 118 with the third station crew was launched on 17 November
1973 by the "Saturn-1B" booster rocket. The third crew included Gerald
Carr (commander), Edward Gibson (scientist and astronaut) and William Pogue
(copilot). None of the crew members had had any speceflight experience.
The flight of this crew was initially calculated at 56 days. Later, after
studying the post-flight medical indicators of the first and second crews,
the medical specialists considered it possible to increase the stay of the
third crew on the station to 84 days. After 56 days the astronauts were
given a weekly medical examination, and permission to extend the flight for
the next week was granted on the basis of its results. Tnitially the primary
mission for the third crew was to study the earth's natural resources, but
later the primary mission was defined as observations of the comet Kohoutek.
The launching of the third crew was delayed from 26 October to 10 November
1973 in order that the manning of the station would fall into the period in
which the comet would come closest to the Sun and the earth. The third crew
devoted two of the four planned walks in open space to observations of the
comet: directly before the directly after it passed through the perihelion
(28 December 1973). No significant repair operations were planned for the
third crew. The payload of the No 118 transport ship (990 kg) basically
included equipment and specimens for scientific research. The transport
ship was loaded with food stores (27 kg of especially high-calorie powdered
sticks used in the production of candy with an aromatic glaze) inasmuch as
the stores on board the station were not sufficient for the prolonged stay.
The transport ship also carried a tank with coolant to replenish the cooling
system in which a leak had occurred. The delay in launching the No 118 ship
from 10 to 16 November was caused by failure of the booster rocket.
The perigee of the initial orbit of the transport ship with the third crew
was 153 km, and the apogee was 324 lan. As a result of five maneuvers the
transport spacecraft rendezvoused with the station, and eight hours after
launching, having flown around the station for examination and television
204.
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
survey, the astronauts docked with it. Docking was successful on the
second attempt. All of the astronauts experienced symptoms of motion sick-
ne�.:s. Pogue vomited. The crew devoted the first days on the station to
demothballing the equipment and preparing for scientific research. All
of the operations took place somewhat behind schedule.
The delay was observed during the entire flight (the fitness of the ast'co--
nauts approached the calculated level only in the second half of the flight).
Obviously, the individual peculiarities of the members of the third crew
were expressed. They were slow; th~:y rather frequently made errors; they
requested additional r.est periods; and they did not work with any zeal or
'enthusiasm like the preceding crews. Possibly one of the reasons for be-
ing behind schedule was the absence of a demanding commander with space-
flig:r;c experience such as Conrad and Bean who commanded the first and second
crews. However, it turned out that the we.:k schedules for the third crew
were based on the achievements of the second, which obviously set a record
and were not the norm.
On 19 November Pogue put the coolant brought from earth in the cooling sys-
tem. To do this, it was necessary to punch a hole in the main line using
' a device resembling a syringe. A valve was seated in the opening, and the
coolant was introduced through it.
On 22 November, Pogue and Jibson completed a walk in
hours 35 minutes. They replaced five film holders in
repaired the antenna drive of the microwave probe for
resources, and th,y mounted samples of heat shielding
structure outside the station in order to investigate
an~ solar radiation on them.
)pen space lasting 6
the ATM complex. They
investigating natural
coatings on the girder
the effects of cosmic
On. 23 November, as a result of the overheating of bearings, it was necessary
to shut down the No 1 power gyroscope in the CMG orientarion system. Accord-
ingly, it was necessary to use the TACS system for subsequent changes in
orientation of the station, which led to highly significant overconsumption
of the compressed nitrogen for the engines of the system. Subsequently fail-
ures also began to be observed in the No 2 power gyroscope. This made it
necessary to refrain from natural resources observation sessions for several
days because they required a change in orientation of the st.ation. There
- was a danger of having to shut down power gyroscope No 2. Then a premature
return of the crew to the earth would have become unavoidable, for orientation
could be .,taintained only by using the TACS system engines, and the compressed
nitrogen reserve was extremely limit'ed for this. In spite of the failures,
power gyroscope No 2 operated to the very end of the crew's missions on
board the station. The compressed nitrogen also lasted the entire time.
On 23 November, the crew began .:s observations of the sun using the ATM
complex; they began studies of natural resources with the EREP complex;
they took photographs with manual cameras and performed other experiments,
205.
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
FOR OFFICIAL USE ONLY
, . ~
Third Skylab Crew: (left to right) Carr, Pogue, Gibson
including visual recording of the beam from a ground laser and observation
of the flight of the "Minuteman" strategic missile. Most importantly, they
took pictures of the comet Kohoutek--first by handheld cameras, then on
19 December when the comet approached the sun (and the earth), with ATM
instruments. The astronauts devoted a great deal of time to exercises on
the bicycle and the treadmill (the first and second crews did not have this
treadmill), studies in the lower body negative pressure device, tests in
_ the cupolometric chair, and so on.
The second and third walks in open space were performed on 25 and 29 Decem-
ber to photograph the comet Kohoutek using two cameras loaded with film
and sensitive to ultraviolet radiation. On 25 December, Carr and Pogue
took a 7 hour walk; on 29 December Carr and Gibson took a 3 hour 28 minute
walk.
On New Year's Eve some of the results of thP work of the astronauts were
suruned up. Out of the 24 sessions studying natural resources planned for
November-December 1973, only 19 were performed; 196 hours were spent on
~ medical experiments instead of the 228 proposed under the program; 140 hours
were spent on other scientific experiments (in addition to the observations
using the ATM complex) instead of 235. The only area in which the astro-
nauts overfulfilled the initial program was in observing the sun and the
comet Kohoutek using the ATM complex. In November-December the astronauts
worked an average of 24 man-hours a day instead of 26-29 man-hours as planned.
In January 1974, the fitness of the astronauts was improved. For example,
on 8 January they worked more than 30 man-hours.
206
FOR OFFICIAL USE ONLY
APPROVED FOR RELEASE: 2007/02/08: CIA-RDP82-00850R000100090025-4

APPROVED FOR RELEASE: 2007/02108: CIA-RDP82-00850R000100090025-4
cn
~
O~
r-I
G

'd
N
~
U
~
cd
r-~
1J
W
ro
~
U
N
U
~
a
N
4-1
w

O
cn
I
G
0
z
FOR OFFICIAL
USE ONLY
~ rn
U)

'
e-1
r-I
t- tfl M W
01 00 LIl
00
. r-i 00
-IY
-rq
1~.1
Of~
r-1 00 L/1 m rl
ri 00 rl
0~0
Ol b t/1 ~D 00
Ul N
1.1
-rl
~rl
--T 00 -.Y' 00 tV
cn 00 O
00 N O rl 00
-t M
�
N
~
~ r-I
~
rl rl r-I
~-I
~
~
N
r
-1
2
~
H
O
C.
~
o 0
0
0
~
o 0 o m N
m o 0
0
op o a o 0
0 0
r-1 O
r-i I, -It :T t-
u'1 N 00
N
%It I- N r--I ON
-zr r-1
1-1
U �rl
. . . . .
. .
.
.
.
.
. . .
. .
N
q 1.~
O u'1C01.io0
1000
0
M
OCOO
N
1U
N o0
�rl
H R1
rl 01 .4 -rl M
m m
kO
r-i N Ol O 01
1%O
~.J
F'.
r-I ~
JJ r{ r-1
�H
f-1
�r~
.
0

~
~
N
GO O c~'1 r-1
O
t- r-I ~7'
O
O O~.O O1% O\
M v1
N
rl I~ QO ul U m
00 O1, ul
O
O m O M O%D
N O
W
b0
~-O N-T M �rl O
a0 N o0
c'1
m 01 r-i L!1 N
r-i M
�
~
a
r-i

o
O r--l r--~
't
~
r
i
N
~
v
N
.A
G
O
J-1
O
N
O
�r-j 0
N
OJ
%~D~-I u'1 Lr1 L' "D
u'1 m I-,
O1%
4..3 I- O I- O ON
O% ~10
fl
b0
O v'1 I- m N"i
1.0 -It O
u'1
cd cr1 O O O vl
m u1
R!
~ri
r-i .-1 Il- r-i r1 O
Lrl r-i 00
.7
ti r-i r-1 O1% Lf1 r-I
I, ri
LI
}-1
N u'1 N rl
t/1
v'1
cd
N
c'1 M
c'1
rl
c"1
w
a
i
ro
a~
~
~
.H
.
o
~
o0
0
�H
,-a
x
o 0
o
w
u r- o 0
a)
ooooIt
ooLn
q
oooLnooooo000
4-1
CO c*1 crt O c*1
O cY1 M
�rl
M O m %D ~Y' c+'1 Lrl ul ~.O
3
.O r-q Lr1 r1 m
00 H H
rl m m
cY1 r-i ir1 ul %O
N
O
2
2
z
~4
r-i on
ao
tn a+J 4+ > >
u u
w
Cd W a cu
u u o o
a~ a)
0
4.
tnOOZZ
(aA
U
N
G
~O O% O%,O O
N Cl
m ~'O O
d' %O
11
~
N r--I r-1
r-i r-1 r1
N
N N N N r-i
r-1 r1
co
Q
r

N
~
~
td cd fU
N
(ti td m
R1
fa
1.1
4-1 4-7
c:
� " 4 11
IJ
Q)
N
Q1 ~ ri ~ ~I
!4
"
oz r-i r-i
+-J
?C
b0 A C1 W v
U A (1)
~A
~
~
N f~ ~ ~ A
U N
cn
u
A~''~ A
C`') c'i O
c
*
i
U CY1 A AC''1
c'1 A
m G
C
U
Gpq
U
~
~
U
O
N
r

q
I
G
i.~ v
- G

q~
Pq
R) to (b fb fo
fSS Ra ~t
(o
fb fb fti ;j w fb
R) 0
rl 11 1-+ 11 p
11 11 O
1-)
H 1-J }-i O}-+ 4-1
11 p
1.1 �rl O�H O
�ri �rl .C
�rl
" �ri O U O�rl
'rq O